CN108182319B - Supersonic velocity integrated spray pipe design method - Google Patents
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Abstract
A design method of a supersonic velocity integrated spray pipe relates to the field of wind tunnel tests; the method comprises the following steps: establishing a spray pipe model, which comprises a contraction section, an expansion section, a test section and a boundary layer; step two, solving a TG section curve according to a characteristic line equation of the TG section curve; obtaining an AD section curve according to a characteristic line equation of the AD section curve to obtain a complete curve of the outer wall of the expansion section; step three, calculating the displacement thickness of the boundary layer; obtaining a boundary layer curve; step four, obtaining a complete curve of a contraction section; step five, obtaining a complete curve of the test section; the invention increases the test area, and the parameters of the test section such as Mach number root mean square deviation, axial Mach number gradient and airflow deflection angle meet the advanced indexes of the national military standard.
Description
Technical Field
The invention relates to the field of wind tunnel tests, in particular to a design method of a supersonic velocity integrated spray pipe.
Background
At present, in the supersonic wind tunnel test, because the Mach angle of the outlet of the spray pipe is small, the area of an effective test uniform area is small, and in order to avoid the test model being exposed outside the test uniform area, only a small test model can be adopted. The test data obtained by the smaller test model in the wind tunnel has certain deviation with the test data obtained by the actual aircraft model, and the test precision is influenced. Meanwhile, a small test uniform area limits the model to continuously change the attitude angle, and the running cost of the wind tunnel is increased.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide a design method of an ultrasonic-speed integrated spray pipe, so that a test area is enlarged, and parameters such as the Mach number root-mean-square deviation, the axial Mach number gradient, the airflow deflection angle and the like of a test section meet the advanced indexes of the national military standard.
The above purpose of the invention is realized by the following technical scheme:
a design method of a supersonic velocity integrated spray pipe comprises the following steps:
step one, establishing a spray pipe model; comprises a contraction section, an expansion section, a test section and a boundary layer; wherein, the contraction section, the expansion section and the test section are sequentially connected end to end along the axial direction; the boundary layer is coated on the outer walls of the expansion section and the test section; the connecting part of the contraction section and the expansion section is a throat; the position of the throat corresponding to the outer wall of the spray pipe is a T point; the position of the joint of the expansion section and the test section, which corresponds to the outer wall of the spray pipe, is a point D; one end of the contraction section axially far away from the expansion section is an inlet end; one end of the expansion section axially far away from the contraction section is an outlet end;
presetting a maximum expansion angle theta and a Mach number M of an expansion section and the diameter of an outlet end of the expansion section; selecting a point corresponding to the maximum expansion angle theta in the expansion section, and defining the point as a G point; taking the point G as a starting point, and taking a point A on the outer wall of the expansion section along the direction pointing to the test section; the GA section is a conic section; establishing a coordinate system oxy; respectively establishing a characteristic line equation of an AD section curve and a characteristic line equation of a TG section curve according to the coordinate system oxy; obtaining a TG section curve according to a characteristic line equation of the TG section curve; obtaining an AD section curve according to a characteristic line equation of the AD section curve;
connecting the G point of the TG section curve and the A point of the AD section curve in a straight line; obtaining a complete curve of the outer wall of the expansion section;
step three, establishing a Karman momentum integral equation to calculate the momentum thickness delta' of the boundary layer; calculating the displacement thickness delta of the boundary layer according to the momentum thickness delta'; namely a boundary layer curve;
step four, obtaining the downstream slope of the T point according to the characteristic line equation of the TG section curve in the step two; the slope of the downstream of the point T is the same as that of the upstream of the point T; obtaining a complete curve of the contraction section;
presetting an under-expansion correction factor lambda; the curve of the outer wall of the test section is a straight line section; obtaining the slope of the upstream of the point D according to the characteristic line equation of the curve of the section AD in the step (II); the slope of the test section is the slope of the upstream of the point D multiplied by an under-expansion correction factor lambda; a complete curve of the test segment is obtained.
In the above method for designing a supersonic velocity integrated nozzle, in the step (ii), the method for establishing the coordinate system oxy includes:
and the point T is used as the origin of coordinates, the positive direction of the x axis is the direction pointing to the outlet end along the axial direction, and the square of the y axis is the vertical upward direction.
In the above method for designing a supersonic velocity integrated nozzle, in the step (ii), the characteristic line equation of the AD section curve is:
the characteristic line equation of the curve of the TG section is as follows:
in the formula, x is the abscissa of a coordinate system oxy;
y is the ordinate of the coordinate system oxy;
the gas specific heat ratio in the gamma nozzle.
In the above method for designing a supersonic velocity integrated nozzle, in the step (three), the method for calculating the momentum thickness δ' of the boundary layer by using the karman momentum integral equation includes:
wherein H is the boundary layer form factor;
Cfis the coefficient of friction.
In the above method for designing a supersonic velocity integrated nozzle, in the step (three), the method for calculating the displacement thickness δ is as follows:
δ＝Hδ′ (4)。
compared with the prior art, the invention has the following advantages:
(1) the unbonded line designed by the characteristic line method in the step 1 is continuous in slope, and the air flow does not generate wave system when flowing in the spray pipe;
(2) the boundary layer correction method in the step 2 is adopted, the flow rule of the air flow is met, and the flow field quality of the outlet of the spray pipe is excellent;
(3) the invention adopts the connection mode of the step 3, so that the slopes of the contraction section and the expansion section of the spray pipe are continuous, and the flow cannot be separated when the airflow flows through the T point of the throat;
(4) the optimization method of the step 4 and the step 5 is adopted, so that the DQ of the outlet of the spray pipe has no obvious expansion wave system and shock wave, and the test area is increased from CDF to CDSN. Parameters such as Mach number root mean square deviation, axial Mach number gradient, airflow deflection angle and the like of the test section meet the advanced indexes of the national military standard.
Drawings
FIG. 1 is a schematic view of a supersonic velocity integrated nozzle of the present invention;
FIG. 2 is a schematic diagram of the design process of the supersonic velocity integrated nozzle of the present invention.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples:
as shown in fig. 2, which is a schematic flow chart of the design of the supersonic velocity integrated nozzle, it can be known that a design method of the supersonic velocity integrated nozzle includes the following steps:
step one, establishing a spray pipe model; comprises a contraction section 1, an expansion section 2, a test section 3 and a boundary layer 4; wherein, the contraction section 1, the expansion section 2 and the test section 3 are sequentially connected end to end along the axial direction; the boundary layer 4 is coated on the outer walls of the expansion section 2 and the test section 3; the connecting part of the contraction section 1 and the expansion section 2 is a throat; as shown in fig. 1, which is a schematic view of a supersonic velocity integrated nozzle, it can be known that the position of the throat corresponding to the outer wall of the nozzle is a point T; the position of the joint of the expansion section 2 and the test section 3, which corresponds to the outer wall of the spray pipe, is a point D; one end of the contraction section 1 axially far away from the expansion section 2 is an inlet end; one end of the expansion section 2 axially far away from the contraction section 1 is an outlet end;
presetting a maximum expansion angle theta and a Mach number M of the expansion section 2 and the diameter of an outlet end of the expansion section 2; selecting a point corresponding to the maximum expansion angle theta in the expansion section 2, and defining the point as a G point; taking the point G as a starting point, and taking a point A on the outer wall of the expansion section 2 along the direction pointing to the test section 3; the GA section is a conic section; establishing a coordinate system oxy; the method for establishing the coordinate system oxy comprises the following steps:
and the point T is used as the origin of coordinates, the positive direction of the x axis is the direction pointing to the outlet end along the axial direction, and the square of the y axis is the vertical upward direction.
Respectively establishing a characteristic line equation of an AD section curve and a characteristic line equation of a TG section curve according to the coordinate system oxy; obtaining a TG section curve according to a characteristic line equation of the TG section curve; obtaining an AD section curve according to a characteristic line equation of the AD section curve;
the characteristic line equation of the AD section curve is as follows:
the characteristic line equation of the curve of the TG section is as follows:
in the formula, x is the abscissa of a coordinate system oxy;
y is the ordinate of the coordinate system oxy;
the gas specific heat ratio in the gamma nozzle.
Connecting the G point of the TG section curve and the A point of the AD section curve in a straight line; obtaining a complete curve of the outer wall of the expansion section 2;
step three, establishing a Karman momentum integral equation to calculate the momentum thickness delta' of the boundary layer 4; and calculating the displacement thickness delta of the boundary layer 4 according to the momentum thickness delta'; namely the boundary layer 4 curve;
the method for calculating the momentum thickness delta' of the boundary layer (4) by the Karman momentum integral equation is as follows:
wherein H is the boundary layer form factor;
Cfis the coefficient of friction.
The calculation method of the displacement thickness delta comprises the following steps:
δ＝Hδ′ (4)。
step four, obtaining the downstream slope of the T point according to the characteristic line equation of the TG section curve in the step two; the slope of the downstream of the point T is the same as that of the upstream of the point T; obtaining a complete curve of the contraction section 1;
presetting an under-expansion correction factor lambda; the curve of the outer wall of the test section 3 is a straight line section; obtaining the slope of the upstream of the point D according to the characteristic line equation of the curve of the section AD in the step (II); the slope of the test section 3 is the slope of the upstream of the point D multiplied by an under-expansion correction factor lambda; a complete curve of test segment 3 was obtained. And optimizing the correction factor lambda to ensure that the outlet D of the spray pipe and the test section DS have no obvious expansion wave and shock wave, thereby completing the molded line design of the supersonic velocity integrated spray pipe.
Taking a point C at the axis of the nozzle, wherein CD is equal to the radius of the outlet end of the expansion section 2 divided by sin beta; β ═ arcsin (1/M); the points F and C are radially symmetrical along the outlet of the expansion section 2; s, N points are respectively taken at the tail end of the test section 3 along the radial direction; the present invention increases the test area from CDF to CDSN. Parameters such as Mach number root mean square deviation, axial Mach number gradient, airflow deflection angle and the like of the test section meet the advanced indexes of the national military standard.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (5)
1. A design method of a supersonic velocity integrated spray pipe is characterized by comprising the following steps: the method comprises the following steps:
step one, establishing a spray pipe model; comprises a contraction section (1), an expansion section (2), a test section (3) and a boundary layer (4); wherein the contraction section (1), the expansion section (2) and the test section (3) are sequentially connected end to end along the axial direction; the boundary layer (4) is coated on the outer walls of the expansion section (2) and the test section (3); the connecting part of the contraction section (1) and the expansion section (2) is a throat; the position of the throat corresponding to the outer wall of the spray pipe is a T point; the position of the joint of the expansion section (2) and the test section (3) corresponding to the outer wall of the spray pipe is a point D; one end of the contraction section (1) axially far away from the expansion section (2) is an inlet end; one end of the expansion section (2) axially far away from the contraction section (1) is an outlet end;
presetting a maximum expansion angle theta and a Mach number M of the expansion section (2) and the diameter of an outlet end of the expansion section (2); selecting a point corresponding to the maximum expansion angle theta in the expansion section (2), and defining the point as a G point; taking a point A on the outer wall of the expansion section (2) along the direction pointing to the test section (3) by taking the point G as a starting point; the GA section is a conic section; establishing a coordinate system oxy; respectively establishing a characteristic line equation of an AD section curve and a characteristic line equation of a TG section curve according to the coordinate system oxy; obtaining a TG section curve according to a characteristic line equation of the TG section curve; obtaining an AD section curve according to a characteristic line equation of the AD section curve;
connecting the G point of the TG section curve and the A point of the AD section curve in a straight line; obtaining a complete curve of the outer wall of the expansion section (2);
step three, establishing a Karman momentum integral equation to calculate the momentum thickness delta' of the boundary layer (4); and calculating the displacement thickness delta of the boundary layer (4) from the momentum thickness delta'; namely the curve of the boundary layer (4);
step four, obtaining the downstream slope of the T point according to the characteristic line equation of the TG section curve in the step two; the slope of the downstream of the point T is the same as that of the upstream of the point T; obtaining a complete curve of the contraction section (1);
presetting an under-expansion correction factor lambda; the curve of the outer wall of the test section (3) is a straight line section; obtaining the slope of the upstream of the point D according to the characteristic line equation of the curve of the section AD in the step (II); the slope of the test section (3) is the slope of the upstream of the point D multiplied by an under-expansion correction factor lambda; a complete curve of the test section (3) is obtained.
2. The design method of the supersonic velocity integrated nozzle according to claim 1, characterized in that: in the step (two), the method for establishing the coordinate system oxy comprises the following steps:
and the point T is used as the origin of coordinates, the positive direction of the x axis is the direction pointing to the outlet end along the axial direction, and the square of the y axis is the vertical upward direction.
3. The design method of the supersonic velocity integrated nozzle according to claim 2, characterized in that: in the step (two), the characteristic line equation of the AD section curve is as follows:
the characteristic line equation of the curve of the TG section is as follows:
in the formula, x is the abscissa of a coordinate system oxy;
y is the ordinate of the coordinate system oxy;
the gas specific heat ratio in the gamma nozzle.
4. The design method of the supersonic velocity integrated nozzle according to claim 1, characterized in that: in the step (III), the method for calculating the momentum thickness delta' of the boundary layer (4) by using the Karman momentum integral equation comprises the following steps:
wherein H is the boundary layer form factor;
Cfis the coefficient of friction.
5. The design method of the supersonic velocity integrated nozzle according to claim 4, is characterized in that: in the step (III), the calculation method of the displacement thickness delta comprises the following steps:
δ＝Hδ′ (4)。
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| CN115389155B (en) * | 2022-07-29 | 2024-08-06 | 中国航天空气动力技术研究院 | Hypersonic gas-liquid-solid multiphase flow molded surface spray pipe design method |
| CN115048730B (en) * | 2022-08-15 | 2022-10-21 | 中国人民解放军国防科技大学 | Axial symmetry supersonic velocity spray pipe optimization design method and device based on grid displacement |
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