CN103617338A - Method and device for rapidly calculating hypersonic viscosity force of aircraft - Google Patents

Method and device for rapidly calculating hypersonic viscosity force of aircraft Download PDF

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CN103617338A
CN103617338A CN201310718622.3A CN201310718622A CN103617338A CN 103617338 A CN103617338 A CN 103617338A CN 201310718622 A CN201310718622 A CN 201310718622A CN 103617338 A CN103617338 A CN 103617338A
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viscous
surface cell
hypersonic
aircraft
cell
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龚安龙
纪楚群
刘周
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China Academy of Aerospace Aerodynamics CAAA
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Abstract

The invention discloses a method and device for rapidly calculating hypersonic viscosity force of an aircraft. The method comprises the following steps: S1. solving an inviscid Euler equation by CFD (Computational Fluid Dynamics) to obtain the physical parameters of an inviscid flow field on the hypersonic surface of the aircraft, wherein the physical parameters of the inviscid flow field on the surface include the pressure, the heat insulating temperature and the speed of the surface; S2. gaining Reynolds numbers of all surface units of the hypersonic surface of the aircraft; and S3. getting the hypersonic viscosity force of the aircraft according to the physical parameters of inviscid flow field on the surface and the Reynolds numbers of all surface units of the surface. The device comprises an obtaining apparatus, a gaining apparatus and a getting apparatus. By the technical scheme, the calculation efficiency and the calculation accuracy of the hypersonic viscosity force of the aircraft in the initial design of engineering are enhanced and the using cost of the engineering is lowered.

Description

Method and apparatus for quick calculating aircraft hypersonic turbulence viscous power
Technical field
The invention belongs to aeromechanics technology field, particularly a kind of method and apparatus for quick calculating aircraft hypersonic turbulence viscous power.
Background technology
Significantly raising and CFD(Computational Fluid Dynamics along with the operational speed of a computer, computational fluid dynamics) being gradually improved of method, the CFD method based on without sticky Euler equation can accurately, promptly complete the calculating without viscosity flow field characteristic.And complete Navier-Stokes equation CFD method based on viscosity obtains more high precision and viscous sublayer flow characteristics and still needs to pay very large cost: numerous and diverse high-quality grid generates, flow field Complete Convergence very big consuming time etc.Therefore in complex aircraft profile initial stage Selection and Design, the prediction of flow field characteristic mainly still adopt high-level efficiency and have good accuracy without sticky Euler equation CFD method, and viscous force part conventionally adopt with without viscosity flow field result completely independently engineering experience modification method calculate, as equivalent plate laminar flow Blassius approximation method and turbulent flow Van Driest II method etc.These method counting yielies are high, and engineering is applied to have good predictive ability and accuracy in certain Mach number and reynolds number range, still very poor for the mobile precision of prediction of hypersonic turbulence viscous.In hypersonic flight design, develop reference temperature method abroad and carried out the calculating of viscous force, but still using free inlet flow conditions as the frictionless flow parameter outside viscous layer, do not consider complicated hypersonic impact of streaming viscous layer outer rim flow parameter, so accuracy is not high.
Summary of the invention
In order to solve the problem of prior art, the embodiment of the present invention provides a kind of method and apparatus for quick calculating aircraft hypersonic turbulence viscous power.Described technical scheme is as follows:
On the one hand, provide a kind of method for quick calculating aircraft hypersonic turbulence viscous power, described method comprises:
Step S1, to adopting Computational Fluid Dynamics method to obtain the hypersonic surface of described aircraft without viscosity flow field physical parameter without sticky Euler equation, wherein, described surface comprises without viscosity flow field physical parameter: the adiabatic temperature on the pressure on surface, surface and the speed on surface;
Step S2, obtains the Reynolds number of all surface unit on the hypersonic surface of described aircraft;
Step S3, obtains the hypersonic viscous force of described aircraft according to described surface without the Reynolds number of all surface unit on viscosity flow field physical parameter and described surface.
In method as above, preferably,, described step S2 specifically comprises:
Step S20, chooses the hypersonic surface cell of described aircraft, according to the surface streamline through described surface cell, obtains the streamline length between described surface cell and the starting point of described surface streamline;
Step S21, obtains the reference temperature in viscous boundary layer according to the speed of the adiabatic temperature of described surface cell, described surface cell and the hypersonic surface temperature of described aircraft;
Step S22, obtains the coefficient of viscosity in described viscous boundary layer according to the reference temperature in described viscous boundary layer;
Step S23, obtains the density in described viscous boundary layer according to the reference temperature in the pressure of described surface cell and described viscous boundary layer;
Step S24, obtains the Reynolds number of described surface cell according to the speed of the density in described viscous boundary layer, coefficient of viscosity, described surface cell, described streamline length;
Circulation performs step S21, step S22, step S23 and step S24, obtains the Reynolds number of all surface unit on the hypersonic surface of described aircraft.
In method as above, preferably, the surface streamline of the described surface cell of process in described step S20 and the starting point of described surface streamline all can be by described surface cell the speed of the coordinate in rectangular coordinate system in space and described surface cell according to streamline, define and adopt quadravalence to show that Runge Kutta method tries to achieve.
In method as above, preferably, described step S21 specifically comprises:
According to
Figure BDA0000444849870000021
obtain the reference temperature in viscous boundary layer;
Described step S22 specifically comprises:
According to obtain the coefficient of viscosity in described viscous boundary layer;
Described step S23 specifically comprises:
According to obtain the density in described viscous boundary layer;
Described step S24 specifically comprises:
According to
Figure BDA0000444849870000031
obtain the Reynolds number of described surface cell;
Wherein, p e, T eand u ebe respectively the speed of the pressure of described surface cell, the adiabatic temperature of surface cell and surface cell, T *for described reference temperature, T wfor described aerocraft real surface temperature, the mobile Mach number that Me is surface cell,
Figure BDA0000444849870000032
γ value positive number, is specific heat ratio, and R value positive number is gas law constant;
μ *for described coefficient of viscosity, T 0=288K, μ 0=1.789 * 10 -5kg/ (ms);
ρ *for described density;
Figure BDA0000444849870000035
for the Reynolds number of described surface cell, s is described streamline length.
In method as above, preferably, described step S3 specifically comprises:
Step S31, obtains the viscous friction force coefficient of described surface cell according to the Reynolds number of described surface cell;
Step S32, obtains the viscous force of described surface cell according to the area of the density in the speed of the viscous friction force coefficient of described surface cell, described surface cell, described viscous boundary layer and described surface cell;
Circulation execution step S31 and step S32, and the viscous force of all surface unit of aircraft surface is sued for peace, the hypersonic viscous force of described aircraft obtained.
In method as above, preferably, described step S31 specifically comprises:
If the Reynolds number of described surface cell is less than or equal to transition Reynolds number, the viscous friction force coefficient of described surface cell otherwise the viscous friction force coefficient of described surface cell
c f * = 0.0592 ( Re * s ) 0.2 ;
Described step S32 specifically comprises:
According to
Figure BDA0000444849870000036
obtain the viscous force of described surface cell;
Wherein, Re trfor transition Reynolds number, meet relational expression
Figure BDA0000444849870000037
;
τ is the viscous force of described surface cell, A iarea for described surface cell.
On the other hand, provide a kind of device for quick calculating aircraft hypersonic turbulence viscous power, described device comprises:
Obtain device, for adopting Computational Fluid Dynamics method to obtain the hypersonic surface of described aircraft without viscosity flow field physical parameter to the sticky Euler equation of nothing, wherein, described surface comprises without viscosity flow field physical parameter: the adiabatic temperature on the pressure on surface, surface and the speed on surface;
Acquisition device, for obtaining the Reynolds number of all surface unit on the hypersonic surface of described aircraft;
Auto levelizer, the Reynolds number of all surface unit on the described surface obtaining without viscosity flow field physical parameter and described acquisition device for the surface that obtains according to described acquisition device obtains the hypersonic viscous force of described aircraft.
In device as above, preferably, described acquisition device comprises:
The first acquiring unit, for choosing the hypersonic surface cell of described aircraft, obtains the streamline length between described surface cell and the starting point of described surface streamline according to the surface streamline through described surface cell;
Second acquisition unit, for obtaining the reference temperature in viscous boundary layer according to the speed of the adiabatic temperature of described surface cell, described surface cell and the hypersonic real surface temperature of described aircraft;
The 3rd acquiring unit, for obtaining the coefficient of viscosity in described viscous boundary layer according to the reference temperature in described viscous boundary layer;
The 4th acquiring unit, obtains the density in described viscous boundary layer for the reference temperature of obtaining according to the pressure of described surface cell and described second acquisition unit;
The 5th acquiring unit, the streamline length of obtaining for the density of obtaining according to described the 4th acquiring unit, the coefficient of viscosity that described the 3rd acquiring unit obtains, the speed of described surface cell, described the first acquiring unit obtains the Reynolds number of described surface cell;
Obtain cycling element, be used for making described the first acquiring unit, described second acquisition unit, described the 3rd acquiring unit, described the 4th acquiring unit and described the 5th acquiring unit circular flow, obtain the Reynolds number of all surface unit on the hypersonic surface of described aircraft.
In device as above, preferably, described second acquisition unit is specifically for basis
Figure BDA0000444849870000041
obtain the reference temperature in viscous boundary layer;
Described the 3rd acquiring unit is specifically for basis
Figure BDA0000444849870000042
obtain the coefficient of viscosity in described viscous boundary layer;
Described the 4th acquiring unit is specifically for basis
Figure BDA0000444849870000043
obtain the density in described viscous boundary layer;
Described the 5th acquiring unit is specifically for basis obtain the Reynolds number of described surface cell;
Wherein, p e, T eand u ebe respectively the speed of the pressure of described surface cell, the adiabatic temperature of surface cell and surface cell, T *for described reference temperature, T wfor described aerocraft real surface temperature, M efor the mobile Mach number of surface cell,
Figure BDA0000444849870000052
γ value positive number, is specific heat ratio, and R value positive number is gas law constant;
μ *for described coefficient of viscosity, T 0=288K, μ 0=1.789 * 10 -5kg/ (ms);
ρ *for described density;
for the Reynolds number of described surface cell, s is described streamline length.
In device as above, preferably, described that auto levelizer comprises:
First obtains unit, obtains the viscous friction force coefficient of described surface cell for the Reynolds number of the described surface cell that obtains according to described acquisition device;
Second obtains unit, for obtain the viscous force of described surface cell according to the described first area that must arrive the speed of the viscous friction force coefficient that unit obtains, described surface cell, density in described viscous boundary layer and described surface cell;
Obtain cycling element, for making described first to obtain unit and described second and obtain unit circular flow, and the viscous force of all surface unit of aircraft surface is sued for peace, obtain the hypersonic viscous force of described aircraft.
The beneficial effect that the embodiment of the present invention is brought is as follows:
By obtaining the hypersonic viscous force of aircraft according to surface without the Reynolds number of all surface unit on viscosity flow field physical parameter and the hypersonic surface of aircraft, the computational accuracy in hypersonic turbulence viscous flow field and efficiency are effectively compromised, improved the precision of complete engineering experience approximation method, also guaranteed very high counting yield, for current complicated hypersonic aircraft initial stage Selection and Design provides aeroperformance forecasting tool accurately and efficiently simultaneously.
Accompanying drawing explanation
Fig. 1 be the embodiment of the present invention one provide a kind of for the quick schematic flow sheet of the method for calculating aircraft hypersonic turbulence viscous power;
Fig. 2 is the schematic diagram of the aircraft that provides of the embodiment of the present invention one surface cell when hypersonic;
Fig. 3 be the embodiment of the present invention two provide a kind of for the quick structural representation of the device of calculating aircraft hypersonic turbulence viscous power.
Embodiment
For making the object, technical solutions and advantages of the present invention clearer, below in conjunction with accompanying drawing, embodiment of the present invention is described further in detail.
Embodiment mono-
In the initial stage of aircraft profile Selection and Design, complex aircraft profile especially, viscous force part adopts equivalent plate laminar flow Blassius approximation method or turbulent flow Van Driest II method conventionally.Although these method counting yielies are high, engineering is applied to have good predictive ability and accuracy in certain Mach number and reynolds number range, and the viscous force precision of prediction in flowing for hypersonic turbulence viscous is very poor.The embodiment of the present invention provides a kind of method for quick calculating aircraft hypersonic turbulence viscous power for this reason, and referring to Fig. 1, the method flow that the present embodiment provides is specific as follows:
Step S1, to adopting Computational Fluid Dynamics method to obtain the hypersonic surface of aircraft without viscosity flow field physical parameter without sticky Euler equation, wherein, surface comprises without viscosity flow field physical parameter: the adiabatic temperature on the pressure on surface, surface and the speed on surface;
Particularly, the specific implementation of this step can be: adopt in prior art that aircraft is hypersonic streams surface in situation without sticky flow field parameter to adopting CFD method to calculate without sticky Euler equation to obtain, comprising: the adiabatic temperature on the pressure on surface, surface and surperficial speed.Wherein, in CFD method, can be structured grid, can also be any non-structured grid; Numerical method can be method of finite difference, can also be finite volume method; Difference scheme can be the various frictionless flow computation scheme with good stability and resolution.
Step S2, obtains the Reynolds number of all surface unit on the hypersonic surface of aircraft;
Particularly, the implementation of this step comprises the following steps:
Step S20, chooses the hypersonic surface cell of aircraft, according to the surface streamline through surface cell, obtains the streamline length between surface cell and the starting point of surface streamline;
Wherein, referring to Fig. 2, the hypersonic surface of aircraft being divided into a plurality of surface cells (this dividing mode is implemented in step S1), through the surface streamline of surface cell, can adopting by the following method the explicit Runge-Kutta(Runge Kutta of quadravalence) speed of method effects on surface unit carries out time integral and obtains surface streamline.Specific as follows:
According to the definition of streamline, there is following relational expression:
Figure BDA0000444849870000071
Wherein,
Figure BDA0000444849870000072
Figure BDA0000444849870000073
Figure BDA0000444849870000074
be
Figure BDA0000444849870000075
function, t is the time;
(x, y, z) is respectively the point on surface streamline
Figure BDA0000444849870000077
(surface cell) in rectangular coordinate system in space at the component of directions X, at the component of Y-direction with at the component of Z direction;
(u, v, w) is respectively and this point
Figure BDA0000444849870000078
the speed of corresponding surface cell is in the component velocity of directions X, in the component velocity of Y-direction with in the component velocity of Z direction.
Point on surface streamline
Figure BDA0000444849870000079
coordinate be adjacent a little
Figure BDA00004448498700000710
coordinate meet the explicit Runge-Kutta(Runge Kutta of quadravalence) formula, specific as follows:
Figure BDA00004448498700000711
Wherein,
Figure BDA00004448498700000712
Wherein,
Figure BDA00004448498700000713
for surface streamline is at t=n+1 coordinate constantly,
Figure BDA00004448498700000714
for surface streamline is at t=n coordinate constantly, h is step-length, the interval that reflecting time advances.
The starting point coordinate of surface streamline can show that in conjunction with quadravalence Runge-Kutta method backstepping obtains by the point coordinate on certain known surface streamline.
According to the surface streamline of the coordinate of the above-mentioned starting point drawing and this point of process, obtain the streamline length s from starting point to this point.
Step S21, obtains the reference temperature in viscous boundary layer according to the speed of the adiabatic temperature of surface cell, surface cell and the hypersonic real surface temperature of aircraft;
Particularly, according to formula (v), obtain the reference temperature in viscous boundary layer,
T * T e = 1 + 0.32 M e 2 + 0.58 ( T w T e - 1 ) - - - ( v )
Wherein, T *for reference temperature, T wfor aerocraft real surface temperature, M efor the mobile Mach number of surface cell, T efor the adiabatic temperature of surface cell, u efor the speed of surface cell, γ is specific heat ratio, value positive number, and being preferably 1.4, R is gas law constant, value positive number, is preferably 287.13.
M ecan be obtained by formula (vi):
M e = u e γ · R · T e - - - ( vi )
This formula (v) obtains based on reference temperature method.
Step S22, obtains the coefficient of viscosity in viscous boundary layer according to the reference temperature in viscous boundary layer;
Particularly, according to formula (vi), obtain the coefficient of viscosity in viscous boundary layer,
μ * = μ 0 · ( T * T 0 ) 1.5 ( T 0 + 110 T * + 110 ) - - - ( vii )
Wherein, μ *for coefficient of viscosity, T 0=288K, μ 0=1.789 * 10 -5kg/ (ms).
Coefficient of viscosity is determined by reference temperature, adopts Sutherland formula (vii) to calculate.
Step S23, obtains the density in viscous boundary layer according to the reference temperature in the pressure of surface cell and viscous boundary layer;
Particularly, according to formula (viii), obtain the density in viscous boundary layer,
ρ * = P e R · T * - - - ( viii )
Wherein, ρ *for density, p efor the pressure of surface cell, density is calculated by the Ideal-Gas Equation (viii).
Step S24, obtains the Reynolds number of surface cell according to the speed of the density in viscous boundary layer, coefficient of viscosity, surface cell, streamline length;
Particularly, according to formula (ix), obtain the Reynolds number of surface cell,
Re s * = ρ * · u e · s μ * - - - ( ix )
Wherein,
Figure BDA0000444849870000085
for Reynolds number.
According to step S21, step S22, step S23 and step S24, obtain the Reynolds number of surface cell, and then circulation execution step S21, step S22, step S23 and step S24, obtain the Reynolds number of all surface unit on the hypersonic surface of aircraft.
Step S3, obtains the hypersonic viscous force of aircraft according to surface without the Reynolds number of all surface unit on viscosity flow field physical parameter and the hypersonic surface of aircraft.
Particularly, the implementation of this step S3 comprises the following steps:
Step S31, obtains the viscous friction force coefficient of surface cell according to the Reynolds number of surface cell;
Wherein, this step S31 comprises:
If the Reynolds number of surface cell is less than or equal to transition Reynolds number (being now laminar flow), the viscous friction force coefficient of surface cell
Figure BDA0000444849870000091
if the Reynolds number of surface cell is greater than transition Reynolds number (being now turbulent flow), the viscous friction force coefficient of surface cell
Figure BDA0000444849870000092
Wherein, Re trfor transition Reynolds number, meet relational expression .
Step S32, obtains the viscous force of surface cell according to the area of the speed of the viscous friction force coefficient of surface cell, surface cell, density in viscous boundary layer and surface cell;
Particularly, according to formula (x), obtain the viscous force of surface cell;
c f * · ( 0.5 · ρ * · u e 2 ) · A i - - - ( x )
Wherein, the viscous force that τ is surface cell, A iarea for surface cell.
According to step S31 and step S32, obtain the viscous force of surface cell, then circulation execution step S31 and step S32, obtain the viscous force of all surface unit on the hypersonic surface of aircraft, then the viscosity of all surface unit is made every effort to vector obtain the hypersonic viscous force of aircraft.
It should be noted that: reference temperature, coefficient of viscosity and the density in the above-mentioned viscous boundary layer who relates to is all parameters of surface cell.
In sum, first the embodiment of the present invention adopts calculating and obtain without viscosity flow field without sticky Euler equation CFD method of current widespread use, then adopt the speed of the explicit Runge-Kutta method of quadravalence effects on surface to carry out time integral to obtain surface streamline, finally adopt based on surface streamline length Reynolds number and surface and calculate viscous force without the reference temperature method that glues physical parameter.
The method that the embodiment of the present invention provides is by obtaining the hypersonic viscous force of aircraft according to surface without the Reynolds number of all surface unit on viscosity flow field physical parameter and the hypersonic surface of aircraft, in conjunction with Euler equation CFD method, calculate obtain hypersonic without viscosity flow field result, using the flow field parameter on the hypersonic surface of aircraft as viscous layer outer rim flow parameter, without adopting complicated viscosity CFD computing method, better considered actual flow characteristic, there is higher engineering calculation precision, greatly improved counting yield, reduced engineering use cost.
Embodiment bis-
Referring to Fig. 3, the embodiment of the present invention provides a kind of device for quick calculating aircraft hypersonic turbulence viscous power, the method for quick calculating aircraft hypersonic turbulence viscous power providing for carrying out above-described embodiment one, and this device comprises:
Obtain device 201, for adopting Computational Fluid Dynamics method to obtain the hypersonic surface of aircraft without viscosity flow field physical parameter to the sticky Euler equation of nothing, wherein, surface comprises without viscosity flow field physical parameter: the adiabatic temperature on the pressure on surface, surface and the speed on surface;
Acquisition device 202, for obtaining the Reynolds number of all surface unit on the hypersonic surface of aircraft;
Auto levelizer 203, for obtaining the hypersonic viscous force of aircraft according to the Reynolds number that obtains all unit, surface that surface that device 201 obtains obtains without viscosity flow field physical parameter and acquisition device 202.
Wherein, acquisition device 202 specifically comprises:
The first acquiring unit, for choosing the hypersonic surface cell of aircraft, obtains the streamline length between surface cell and the starting point of surface streamline according to the surface streamline through surface cell;
Second acquisition unit, for obtaining the reference temperature in viscous boundary layer according to the speed of the adiabatic temperature of surface cell, surface cell and the hypersonic real surface temperature of aircraft;
Particularly, second acquisition unit is for basis
Figure BDA0000444849870000101
obtain the reference temperature in viscous boundary layer.
The 3rd acquiring unit, for obtaining the coefficient of viscosity in viscous boundary layer according to the reference temperature in viscous boundary layer;
Particularly, the 3rd acquiring unit is for basis obtain the coefficient of viscosity in viscous boundary layer;
The 4th acquiring unit, obtains the density in viscous boundary layer for the reference temperature of obtaining according to the pressure of surface cell and second acquisition unit;
Particularly, the 4th acquiring unit is for basis
Figure BDA0000444849870000103
obtain the density in viscous boundary layer;
The 5th acquiring unit, obtains the Reynolds number of surface cell for the speed of the density obtained according to the 4th acquiring unit, coefficient of viscosity that the 3rd acquiring unit obtains, surface cell, streamline length that the first acquiring unit obtains;
Particularly, the 5th acquiring unit is for basis
Figure BDA0000444849870000104
obtain the Reynolds number of surface cell;
Obtain cycling element, for making the first acquiring unit, second acquisition unit, the 3rd acquiring unit, the 4th acquiring unit and the 5th acquiring unit circular flow, obtain the Reynolds number of all surface unit on the hypersonic surface of aircraft.
Wherein, p e, T eand u ebe respectively the speed of the pressure of surface cell, the adiabatic temperature of surface cell and surface cell, T *for reference temperature, T wfor aerocraft real surface temperature, this surface temperature can be recorded or environment temperature is determined, M by sensor efor the mobile Mach number of surface cell, γ value positive number, is specific heat ratio, and R value positive number is gas law constant; μ *for coefficient of viscosity, T 0=288K, μ 0=1.789 * 10 -5kg/ (ms); ρ *for density;
Figure BDA0000444849870000112
for Reynolds number, s is streamline length.
Wherein, obtaining auto levelizer 203 specifically comprises:
First obtains unit, obtains the viscous friction force coefficient of surface cell for the Reynolds number of the surface cell that obtains according to acquisition device;
Second obtains unit, for obtain the viscous force of surface cell according to the first area that must arrive the speed of viscous friction force coefficient that unit obtains, surface cell, density in described viscous boundary layer and surface cell;
Obtain cycling element, for making first to obtain unit and second and obtain unit circular flow, and the viscous force of all surface unit of aircraft surface is sued for peace, obtain the hypersonic viscous force of aircraft.
Wherein, obtaining the sticky Euler equation employing of 201 pairs of nothings of the device Computational Fluid Dynamics method acquisition hypersonic surface of aircraft specifically can be referring to the associated description of the step S1 in above-described embodiment one without the mode of viscosity flow field physical parameter, acquisition module 202 obtains the mode of Reynolds number of all surface unit on the hypersonic surface of aircraft specifically can be referring to the associated description of the step S2 in above-described embodiment one, auto levelizer 203 according to the Reynolds number that obtains all surface unit on the hypersonic surface of aircraft that surface that device 201 obtains obtains without viscosity flow field physical parameter and acquisition device 202, obtain the mode of the hypersonic viscous force of aircraft specifically can be referring to the associated description of the step S3 in above-described embodiment one, repeat no longer one by one herein.
In sum, the device that the embodiment of the present invention provides is by obtaining the hypersonic viscous force of aircraft according to surface without the Reynolds number of all surface unit on viscosity flow field physical parameter and the hypersonic surface of aircraft, in conjunction with Euler equation CFD method, calculate obtain hypersonic without viscosity flow field result, using the flow field parameter on the hypersonic surface of aircraft as viscous layer outer rim flow parameter, without adopting complicated viscosity CFD computing method, better considered actual flow characteristic, there is higher engineering calculation precision, greatly improved counting yield, reduced engineering use cost.
These are only preferred embodiment of the present invention, in order to limit the present invention, within the spirit and principles in the present invention not all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.

Claims (10)

1. for a method for quick calculating aircraft hypersonic turbulence viscous power, it is characterized in that, described method comprises:
Step S1, to adopting Computational Fluid Dynamics method to obtain the hypersonic surface of described aircraft without viscosity flow field physical parameter without sticky Euler equation, wherein, described surface comprises without viscosity flow field physical parameter: the adiabatic temperature on the pressure on surface, surface and the speed on surface;
Step S2, obtains the Reynolds number of all surface unit on the hypersonic surface of described aircraft;
Step S3, obtains the hypersonic viscous force of described aircraft according to described surface without the Reynolds number of all surface unit on viscosity flow field physical parameter and described surface.
2. method according to claim 1, is characterized in that, described step S2 specifically comprises:
Step S20, chooses the hypersonic surface cell of described aircraft, according to the surface streamline through described surface cell, obtains the streamline length between described surface cell and the starting point of described surface streamline;
Step S21, obtains the reference temperature in viscous boundary layer according to the speed of the adiabatic temperature of described surface cell, described surface cell and the hypersonic real surface temperature of described aircraft;
Step S22, obtains the coefficient of viscosity in described viscous boundary layer according to the reference temperature in described viscous boundary layer;
Step S23, obtains the density in described viscous boundary layer according to the reference temperature in the pressure of described surface cell and described viscous boundary layer;
Step S24, obtains the Reynolds number of described surface cell according to the speed of the density in described viscous boundary layer, coefficient of viscosity, described surface cell, described streamline length;
Circulation performs step S21, step S22, step S23 and step S24, obtains the Reynolds number of all surface unit on the hypersonic surface of described aircraft.
3. method according to claim 2, it is characterized in that, the surface streamline of the described surface cell of process in described step S20 and the starting point of described surface streamline all can be by described surface cell the speed of the coordinate in rectangular coordinate system in space and described surface cell according to streamline, define and adopt quadravalence to show that Runge Kutta method tries to achieve.
4. according to the method in claim 2 or 3, it is characterized in that,
Described step S21 specifically comprises:
According to
Figure FDA0000444849860000021
obtain the reference temperature in viscous boundary layer;
Described step S22 specifically comprises:
According to
Figure FDA0000444849860000022
obtain the coefficient of viscosity in described viscous boundary layer;
Described step S23 specifically comprises:
According to
Figure FDA0000444849860000023
obtain the density in described viscous boundary layer;
Described step S24 specifically comprises:
According to
Figure FDA0000444849860000024
obtain the Reynolds number of described surface cell;
Wherein, p e, T eand u ebe respectively the speed of the pressure of described surface cell, the adiabatic temperature of surface cell and surface cell, T *for described reference temperature, T wfor described aerocraft real surface temperature, M efor the mobile Mach number of surface cell,
Figure FDA0000444849860000025
γ value positive number, is specific heat ratio, and R value positive number is gas law constant;
μ *for described coefficient of viscosity, T 0=288K, μ 0=1.789 * 10 -5kg/ (ms);
ρ *for described density;
Figure FDA0000444849860000026
for the Reynolds number of described surface cell, s is described streamline length.
5. method according to claim 4, is characterized in that, described step S3 specifically comprises:
Step S31, obtains the viscous friction force coefficient of described surface cell according to the Reynolds number of described surface cell;
Step S32, obtains the viscous force of described surface cell according to the area of the density in the speed of the viscous friction force coefficient of described surface cell, described surface cell, described viscous boundary layer and described surface cell;
Circulation execution step S31 and step S32, and the viscous force of all surface unit of aircraft surface is sued for peace, the hypersonic viscous force of described aircraft obtained.
6. method according to claim 5, is characterized in that,
Described step S31 specifically comprises:
If the Reynolds number of described surface cell is less than or equal to transition Reynolds number, the viscous friction force coefficient of described surface cell
Figure FDA0000444849860000031
otherwise the viscous friction force coefficient of described surface cell
c f * = 0.0592 ( Re * s ) 0.2 ;
Described step S32 specifically comprises:
According to
Figure FDA0000444849860000034
obtain the viscous force corresponding with described surface cell;
Wherein, Re trfor transition Reynolds number, meet relational expression
Figure FDA0000444849860000033
;
τ is the viscous force corresponding with described surface cell, A iarea for described surface cell.
7. for a device for quick calculating aircraft hypersonic turbulence viscous power, it is characterized in that, described device comprises:
Obtain device, for adopting Computational Fluid Dynamics method to obtain the hypersonic surface of described aircraft without viscosity flow field physical parameter to the sticky Euler equation of nothing, wherein, described surface comprises without viscosity flow field physical parameter: the adiabatic temperature on the pressure on surface, surface and the speed on surface;
Acquisition device, for obtaining the Reynolds number of all surface unit on the hypersonic surface of described aircraft;
Auto levelizer, the Reynolds number of all surface unit on the described surface obtaining without viscosity flow field physical parameter and described acquisition device for the surface that obtains according to described acquisition device obtains the hypersonic viscous force of described aircraft.
8. device according to claim 7, is characterized in that, described acquisition device comprises:
The first acquiring unit, for choosing the hypersonic surface cell of described aircraft, obtains the streamline length between described surface cell and the starting point of described surface streamline according to the surface streamline through described surface cell;
Second acquisition unit, for obtaining the reference temperature in viscous boundary layer according to the speed of the adiabatic temperature of described surface cell, described surface cell and the hypersonic real surface temperature of described aircraft;
The 3rd acquiring unit, for obtaining the coefficient of viscosity in described viscous boundary layer according to the reference temperature in described viscous boundary layer;
The 4th acquiring unit, obtains the density in described viscous boundary layer for the reference temperature of obtaining according to the pressure of described surface cell and described second acquisition unit;
The 5th acquiring unit, the streamline length of obtaining for the density of obtaining according to described the 4th acquiring unit, the coefficient of viscosity that described the 3rd acquiring unit obtains, the speed of described surface cell, described the first acquiring unit obtains the Reynolds number of described surface cell;
Obtain cycling element, be used for making described the first acquiring unit, described second acquisition unit, described the 3rd acquiring unit, described the 4th acquiring unit and described the 5th acquiring unit circular flow, obtain the Reynolds number of all surface unit on the hypersonic surface of described aircraft.
9. device according to claim 8, is characterized in that,
Described second acquisition unit is specifically for basis obtain the reference temperature in viscous boundary layer;
Described the 3rd acquiring unit is specifically for basis
Figure FDA0000444849860000042
obtain the coefficient of viscosity in described viscous boundary layer;
Described the 4th acquiring unit is specifically for basis obtain the density in described viscous boundary layer;
Described the 5th acquiring unit is specifically for basis
Figure FDA0000444849860000044
obtain the Reynolds number of described surface cell;
Wherein, p e, T eand u ebe respectively the speed of the pressure of described surface cell, the adiabatic temperature of surface cell and surface cell, T *for described reference temperature, T wfor described aerocraft real surface temperature, M efor the mobile Mach number of surface cell,
Figure FDA0000444849860000045
γ value positive number, is specific heat ratio, and R value positive number is gas law constant;
μ *for described coefficient of viscosity, T 0=288K, μ 0=1.789 * 10 -5kg/ (ms);
ρ *for described density;
Figure FDA0000444849860000046
for the Reynolds number of described surface cell, s is described streamline length.
10. device according to claim 9, is characterized in that, described that auto levelizer comprises:
First obtains unit, obtains the viscous friction force coefficient of described surface cell for the Reynolds number of the described surface cell that obtains according to described acquisition device
Second obtains unit, for obtain the viscous force of described surface cell according to the described first area that must arrive the speed of the viscous friction force coefficient that unit obtains, described surface cell, density in described viscous boundary layer and described surface cell;
Obtain cycling element, for making described first to obtain unit and described second and obtain unit circular flow, and the viscous force of all surface unit of aircraft surface is sued for peace, obtain the hypersonic viscous force of described aircraft.
CN201310718622.3A 2013-12-24 2013-12-24 Method and device for rapidly calculating hypersonic viscosity force of aircraft Pending CN103617338A (en)

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