CN114169103A - Propeller modeling method and system based on large propeller disc load working condition - Google Patents
Propeller modeling method and system based on large propeller disc load working condition Download PDFInfo
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Abstract
The invention relates to a propeller modeling method and system based on a large propeller disc load working condition. The method comprises the steps of determining the number of blades of a blade and the radius of a propeller according to design parameters determined by working conditions of the propeller, and simultaneously determining the airfoil profile of a section; determining the induced screw pitch of the section at the position r; determining the optimal ring volume distribution of the hub position and the limited blade number according to the induced pitch; determining the annular induction speed of each station according to the optimal annular quantity distribution and the number of the blades of the paddle; determining the geometric inflow angle of each station according to the inflow speed and the induced screw pitch; determining the initial chord length of each station according to the relative incoming flow speed of each station and the optimal circulation distribution determined by the parameters; corresponding favorable attack angles and lift coefficients under the Reynolds number and the Mach number of each station airfoil; and carrying out three-dimensional modeling on the propeller according to the actual chord length determined by the wing of the section and the lift coefficient, the geometric inflow angle of each station and the pitch angle of each station determined by the favorable attack angle. The invention effectively solves the problem of design precision of the large-propeller-disc load propeller.
Description
Technical Field
The invention relates to the field of propeller design, in particular to a propeller modeling method and system based on a large propeller disc load working condition.
Background
The propeller is a device capable of changing the power of an engine into tension, is widely applied to power systems of various aviation aircrafts and ships due to the advantages of high efficiency, low unit oil consumption, safety and the like, and is an important component of the power systems. The propeller design mainly aims at high efficiency, and the high-efficiency propeller appearance meeting the requirements is designed according to the given flight state and the requirements of tension or power.
The currently developed propeller design methods mainly include two methods, one of which is based on computational fluid dynamics, can adapt to a complex flow field and has high precision, but is limited by the development of computer technology, and has slow computation speed and long overall design period, so that a design scheme cannot be quickly and effectively provided. The other propeller rapid calculation method based on the partial hypothesis, such as the momentum theory, the airfoil theory, the vortex theory and the like of the propeller, can be used for rapid design of the propeller, but the small propeller disc load hypothesis is introduced in order to simplify the relative relation among the speeds during design, so that the design precision is low under the working condition of large propeller disc load, the design tension can be achieved only by continuous iterative optimization after a primary design scheme is given, and the design period is prolonged.
Disclosure of Invention
The invention aims to provide a propeller modeling method and system based on a large propeller disc load working condition, which can quickly design a propeller, effectively solve the problem of design precision of the large propeller disc load propeller and shorten the design period of the propeller.
In order to achieve the purpose, the invention provides the following scheme:
a propeller modeling method based on a large-propeller-disc load working condition comprises the following steps:
determining design parameters according to the working conditions of the propeller, determining the number of blades of the blades and the radius of the propeller according to the design parameters, and simultaneously determining the airfoil shape of a section which is divided from a hub to a tip of the propeller; the design parameters include: designing height, incoming flow speed, design tension and design angular speed;
determining the induced pitch of the section at the position r according to the number of blades of the propeller, the radius of the propeller, the design parameters and the design state; the design state includes: the rotation speed and the density;
determining the optimal ring volume distribution of the hub position and the limited blade number according to the induced pitch of the section at the r position; determining the annular induction speed of each station according to the optimal annular quantity distribution and the quantity of the blades of the paddle;
determining the geometric inflow angle of each station according to the incoming flow velocity and the induced screw pitch of the section at the r position; the geometric inflow angle of each station is the included angle between the incoming flow and the rotating plane;
determining the relative incoming flow velocity of each station according to the geometric inflow angle of each station, the annular induction velocity of each station and the induction screw pitch of the section at the r position;
determining the initial chord length of each station according to the optimal circulation distribution and the relative inflow speed of each station; determining the Reynolds number and the Mach number of the airfoil profile of each station according to the initial chord length of each station, and further determining the corresponding favorable attack angle and lift coefficient under the Reynolds number and the Mach number;
determining the actual chord length according to the lift coefficient, and determining the pitch angle of each station according to the geometric inflow angle and the favorable attack angle of each station;
and carrying out propeller three-dimensional modeling according to the airfoil section, the actual chord length and the pitch angle of the section to complete propeller blade design.
Optionally, the determining the induced pitch of the section at r according to the number of blades of the blade, the radius of the propeller, the design parameter and the design state specifically includes:
using formulas
Determining the induced screw pitch of the section at the position r;
wherein T is the design tension, R is the propeller radius, R0For the hub radius, Γ (r, V') is the optimal ring size distribution considering the hub position and the limited number of blades, ρ is the density, Ω is the design angular velocity, r is the stand of the section, NbV' is the induced pitch of the section at r, which is the number of blades of the blade.
Optionally, determining an optimal ring volume distribution of the hub position and the limited blade number according to the induced pitch of the section at r; and determining the annular induction speed of each station according to the optimal annular quantity distribution and the number of the blades, and specifically comprises the following steps:
using formulas
Determining an optimal ring volume distribution of the hub position and the limited number of blades;
using formulas
Determining the annular induction speed;
wherein, gamma isinfinite(r, V') is the ring quantity distribution taking into account the limited number of blades, F is the Prandtl correction factor, VtThe circumferential induction speed is shown as gamma, and the gamma is the relation between the circumferential quantity and the circumferential induction speed.
Optionally, determining a geometric inflow angle of each station according to the incoming flow velocity and the induced screw pitch of the section at the position r; each station geometric inflow angle is an included angle between an incoming flow and a rotation plane, and specifically comprises the following steps:
using formulas
Determining a geometric inflow angle of each station;
wherein phi is the geometric inflow angle of each station position, V0Is the incoming flow velocity.
Optionally, the determining the relative incoming flow velocity of each station according to the geometric inflow angle of each station, the circumferential induced velocity of each station, and the induced pitch of the section at r includes:
using formulas
Determining the relative incoming flow speed of each station;
wherein, W is the relative incoming flow speed of each station.
Optionally, determining an initial chord length of each station according to the optimal circulation volume distribution and the relative inflow velocity of each station; and determining the Reynolds number and the Mach number of the airfoil profile at each station according to the initial chord length of each station, and further determining the corresponding favorable attack angle and lift coefficient under the Reynolds number and the Mach number, wherein the method specifically comprises the following steps:
using formulas
Determining the initial chord length of each station;
wherein, b0For the initial chord length of each station, ClIs the initial lift coefficient.
Optionally, the determining an actual chord length according to the lift coefficient, and determining a pitch angle of each station according to the geometric inflow angle and the favorable attack angle of each station specifically include:
determining the pitch angle of each station position by using a formula theta as alpha + phi;
where θ is the pitch angle of each station and α is the favored angle of attack.
A propeller modeling system based on a large rotor disk load condition, comprising:
the geometric parameter determining module is used for determining design parameters according to the working conditions of the propeller, determining the number of blades of the blades and the radius of the propeller according to the design parameters, and simultaneously determining the airfoil shape of the section which is divided from the hub to the tip of the propeller; the design parameters include: designing height, incoming flow speed, design tension and design angular speed;
the induced pitch determining module is used for determining the induced pitch of the section at the position r according to the number of the blades of the propeller, the radius of the propeller, the design parameters and the design state; the design state includes: the rotation speed and the density;
the optimal circulation distribution and all station positions annular induction speed determining module is used for determining optimal circulation distribution of the position of the hub and the number of the limited blades according to the induction screw pitch of the section at the r position; determining the annular induction speed of each station according to the optimal annular quantity distribution and the quantity of the blades of the paddle;
the geometric inflow angle determining module of each station is used for determining the geometric inflow angle of each station according to the incoming flow speed and the induced screw pitch of the section at the r position; the geometric inflow angle of each station is the included angle between the incoming flow and the rotating plane;
the relative incoming flow velocity determining module of each station is used for determining the relative incoming flow velocity of each station according to the geometric inflow angle of each station, the annular induction velocity of each station and the induction screw pitch of the section at the r position;
the beneficial attack angle and lift coefficient determining module is used for determining the initial chord length of each station according to the optimal circulation distribution and the relative incoming flow speed of each station; determining the Reynolds number and the Mach number of the airfoil profile of each station according to the initial chord length of each station, and further determining the corresponding favorable attack angle and lift coefficient under the Reynolds number and the Mach number;
the actual chord length and each station pitch angle determining module is used for determining the actual chord length according to the lift coefficient and determining each station pitch angle according to the geometric inflow angle and the favorable attack angle of each station;
and the propeller three-dimensional modeling module is used for carrying out propeller three-dimensional modeling according to the airfoil section, the actual chord length and the pitch angle of the section so as to complete propeller blade design.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
according to the propeller modeling method and system based on the large-blade-disc load working condition, the propeller tension is expressed as a function of the induced pitch in the blade design process, the induced pitch is calculated according to the design tension, and then the actual incoming flow angle and speed of each station are calculated by using parameters such as the induced pitch and the incoming flow speed, so that the error of the actual incoming flow speed direction of each station caused by the small-blade-disc load assumption adopted in the traditional design method is avoided, and the problem of the design precision of the large-blade-disc load propeller is effectively solved. The design method has the advantages of excellent design efficiency and strong robustness, and can greatly shorten the design period of the propeller.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a schematic flow chart of a propeller modeling method based on a large-blade-disc load working condition, provided by the invention;
FIG. 2 is a schematic design flow diagram of a propeller modeling method based on a large-blade-disc load working condition, provided by the invention;
FIG. 3 is a schematic view of an alternative S9000 airfoil of the present invention;
FIG. 4 is a schematic view of a propeller designed using the present invention;
FIG. 5 is a schematic view of a propeller designed using conventional methods;
FIG. 6 is a schematic structural diagram of a propeller modeling system based on a large rotor disk load condition provided by the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a propeller modeling method and system based on a large propeller disc load working condition, which can quickly design a propeller, effectively solve the problem of design precision of the large propeller disc load propeller and shorten the design period of the propeller.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Fig. 1 is a schematic flow chart of a propeller modeling method based on a large rotor disk load condition provided by the present invention, fig. 2 is a schematic flow chart of a design of a propeller modeling method based on a large rotor disk load condition provided by the present invention, and as shown in fig. 1 and fig. 2, a propeller modeling method based on a large rotor disk load condition provided by the present invention includes:
s101, determining design parameters according to the working conditions of the propeller, determining the number of blades of the blades and the radius of the propeller according to the design parameters, and simultaneously determining the airfoil shape of a cross section divided from a hub to a tip of the propeller; the design parameters include: designing height, incoming flow speed, design tension and design angular speed;
as a specific example, the design height H is 0km and the incoming flow velocity V050m/s, 3000N of designed tension T and 157rad/s of designed angular speed omega;
s102, determining the induced pitch of the section at the position r according to the number of blades of the propeller, the radius of the propeller, the design parameters and the design state; the design state includes: the rotation speed and the density;
design parameter determination of blade number NbThe propeller radius R is 1m and the hub radius is 0.01m, 3. Equally dividing the blade into 25 sections from the hub to the tip, and determining the airfoil profile of each section as S9000, wherein the profile refers to the attached figure 3;
s102 specifically comprises the following steps:
using formulas
Determining the induced screw pitch of the section at the position r; i.e. the propeller tension T is a function of the induced pitch V';
wherein T is the design tension, R is the propeller radius, R0For the hub radius, Γ (r, V') is the optimal ring size distribution considering the hub position and the limited number of blades, ρ is the density, Ω is the design angular velocity, r is the stand of the section, NbIs a bladeThe number of sheets, V', is the induced pitch of the section at r.
S103, determining the optimal ring volume distribution of the hub position and the limited blade number according to the induced pitch of the section at the r position; determining the annular induction speed of each station according to the optimal annular quantity distribution and the quantity of the blades of the paddle;
s103 specifically comprises the following steps:
using formulas
Determining an optimal ring volume distribution of the hub position and the limited number of blades;
using formulas
Determining the annular induction speed;
wherein, gamma isinfinite(r, V') is the ring quantity distribution taking into account the limited number of blades, F is the Prandtl correction factor, VtThe circumferential induction speed is shown as gamma, and the gamma is the relation between the circumferential quantity and the circumferential induction speed.
The relationship between the annular quantity and the annular induction speed can be known from the vortex theory:
the airfoil tension dT at r is expressed by the following specific expression:
dT＝ρΓ(rV′)(Ωr-Vt)dr；
namely, it is
Further determining the optimal ring volume distribution of the hub position and the limited blade number;
wherein the content of the first and second substances,
nsis the rotation speed, with the unit of revolutions per second;
s104, determining the geometric inflow angle of each station according to the inflow speed and the induced screw pitch of the section at the r position; the geometric inflow angle of each station is the included angle between the incoming flow and the rotating plane;
s104 specifically comprises the following steps:
using formulas
Determining a geometric inflow angle of each station;
wherein phi is the geometric inflow angle of each station position, V0Is the incoming flow velocity.
S105, determining the relative incoming flow velocity of each station according to the geometric inflow angle of each station, the annular induction velocity of each station and the induction screw pitch of the section at the r position;
s105 specifically comprises the following steps:
using formulas
Determining the relative incoming flow speed of each station;
wherein, W is the relative incoming flow speed of each station.
S106, determining the initial chord length of each station according to the optimal circulation distribution and the relative inflow speed of each station; determining the Reynolds number and the Mach number of the airfoil profile of each station according to the initial chord length of each station, and further determining the corresponding favorable attack angle and lift coefficient under the Reynolds number and the Mach number;
s106 specifically comprises:
using formulas
Determining the initial chord length of each station;
wherein, b0For the initial chord length of each station, ClThe initial lift coefficient is selected according to the actual working condition.
S107, determining actual chord length according to the lift coefficient, and determining the pitch angle of each station according to the geometric inflow angle and the favorable attack angle of each station;
s107 specifically comprises the following steps:
determining the pitch angle of each station position by using a formula theta as alpha + phi;
where θ is the pitch angle of each station and α is the favored angle of attack.
And S108, carrying out propeller three-dimensional modeling according to the airfoil section, the actual chord length and the pitch angle of the section, and completing propeller blade design.
The profile parameters of the obtained propeller are shown in table 1, and the profile of the obtained propeller is shown in fig. 4.
TABLE 1
Under the same design parameters, the propeller is designed by applying a traditional propeller design method which applies a minimum energy loss method introducing a small propeller disc load assumption. The profile parameters of the obtained propeller are shown in table 2, and the profile of the obtained propeller is shown in fig. 5.
TABLE 2
The propellers designed by the two methods are subjected to pneumatic calculation by CFD, and the calculation results are shown in Table 3.
TABLE 3
The calculation result shows that the aerodynamic performance of the propeller designed by the high-efficiency and high-precision design method for the large-propeller-disc-load propeller is better than that of the propeller designed by the traditional method on the whole, wherein the relative error of the tension of the propeller designed by the design method provided by the invention is 0.50%, and is far less than 18.53% of that of the propeller designed by the traditional method. Therefore, the high-efficiency and high-precision design method for the large-propeller-disc-load propeller can effectively solve the problem of design precision of the large-propeller-disc-load propeller and greatly shorten the design period of the propeller.
The invention can effectively meet the design precision requirement of the large-propeller-disc load propeller. The invention controls the radial tension distribution of the propeller blades by introducing the optimal ring amount distribution considering the position of the propeller hub and the limited blade number, removes the assumption of small blade disc load adopted in the traditional design method, establishes the fast design method of the propeller taking the optimal ring amount distribution as input, and effectively solves the problem of the design precision of the propeller, particularly the propeller with large blade disc load. The propeller design method provided by the invention has the advantages of excellent precision, high efficiency and strong robustness.
Fig. 6 is a schematic structural diagram of a propeller modeling system based on a large rotor disk load condition provided by the present invention, and as shown in fig. 6, the propeller modeling system based on the large rotor disk load condition provided by the present invention includes:
the geometric parameter determining module 601 is used for determining design parameters according to the working conditions of the propeller, determining the number of blades of the blades and the radius of the propeller according to the design parameters, and simultaneously determining the airfoil shape of the section which is divided from the hub to the tip of the propeller in an average manner; the design parameters include: designing height, incoming flow speed, design tension and design angular speed;
an induced pitch determining module 602, configured to determine an induced pitch of a cross section at r according to the number of blades, the propeller radius, and the design parameter and the design state; the design state includes: the rotation speed and the density;
an optimal circulation distribution and each station circumferential induction speed determining module 603, configured to determine optimal circulation distribution of the hub position and the limited number of blades according to the induced pitch of the section at r; determining the annular induction speed of each station according to the optimal annular quantity distribution and the quantity of the blades of the paddle;
the geometric inflow angle determination module 604 for each station is configured to determine a geometric inflow angle for each station according to an incoming flow velocity and an induced pitch of a section at r; the geometric inflow angle of each station is the included angle between the incoming flow and the rotating plane;
a relative incoming flow velocity determination module 605 for each station, configured to determine a relative incoming flow velocity of each station according to a geometric incoming flow angle of each station, an annular induced velocity of each station, and an induced pitch of a section at r;
an initial chord length of each station and favorable angle of attack and lift coefficient determining module 606 for determining the initial chord length of each station according to the optimal circulation distribution and the relative incoming flow velocity of each station; determining the Reynolds number and the Mach number of the airfoil profile of each station according to the initial chord length of each station, and further determining the corresponding favorable attack angle and lift coefficient under the Reynolds number and the Mach number;
the actual chord length and each station pitch angle determining module 607 is used for determining the actual chord length according to the lift coefficient and determining each station pitch angle according to the geometric inflow angle and the favorable attack angle of each station;
and the propeller three-dimensional modeling module 608 is used for performing propeller three-dimensional modeling according to the airfoil section, the actual chord length and the pitch angle of the section to complete propeller blade design.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (8)
1. A propeller modeling method based on a large-propeller-disc load working condition is characterized by comprising the following steps:
determining design parameters according to the working conditions of the propeller, determining the number of blades of the blades and the radius of the propeller according to the design parameters, and simultaneously determining the airfoil shape of a section which is divided from a hub to a tip of the propeller; the design parameters include: designing height, incoming flow speed, design tension and design angular speed;
determining the induced pitch of the section at the position r according to the number of blades of the propeller, the radius of the propeller, the design parameters and the design state; the design state includes: the rotation speed and the density;
determining the optimal ring volume distribution of the hub position and the limited blade number according to the induced pitch of the section at the r position; determining the annular induction speed of each station according to the optimal annular quantity distribution and the quantity of the blades of the paddle;
determining the geometric inflow angle of each station according to the incoming flow velocity and the induced screw pitch of the section at the r position; the geometric inflow angle of each station is the included angle between the incoming flow and the rotating plane;
determining the relative incoming flow velocity of each station according to the geometric inflow angle of each station, the annular induction velocity of each station and the induction screw pitch of the section at the r position;
determining the initial chord length of each station according to the optimal circulation distribution and the relative inflow speed of each station; determining the Reynolds number and the Mach number of the airfoil profile of each station according to the initial chord length of each station, and further determining the corresponding favorable attack angle and lift coefficient under the Reynolds number and the Mach number;
determining the actual chord length according to the lift coefficient, and determining the pitch angle of each station according to the geometric inflow angle and the favorable attack angle of each station;
and carrying out propeller three-dimensional modeling according to the airfoil section, the actual chord length and the pitch angle of the section to complete propeller blade design.
2. The method for modeling the propeller according to claim 1, wherein the step of determining the induced pitch of the section at r according to the number of blades of the propeller, the radius of the propeller, the design parameters and the design state comprises:
using formulas
Determining the induced screw pitch of the section at the position r;
wherein T is the design tension, R is the propeller radius, R0For the hub radius, Γ (r, V') is the optimal ring size distribution considering the hub position and the limited number of blades, ρ is the density, Ω is the design angular velocity, r is the stand of the section, NbV' is the induced pitch of the section at r, which is the number of blades of the blade.
3. The propeller modeling method based on the large rotor disc load working condition is characterized in that the optimal ring volume distribution of the hub position and the limited blade number is determined according to the induced pitch of the section at the r position; and determining the annular induction speed of each station according to the optimal annular quantity distribution and the number of the blades, and specifically comprises the following steps:
using formulas
Determining an optimal ring volume distribution of the hub position and the limited number of blades;
using formulas
Determining the annular induction speed;
wherein, gamma isinfinite(r, V') is the ring quantity distribution taking into account the limited number of blades, F is the Prandtl correction factor, VtThe circumferential induction speed is shown as gamma, and the gamma is the relation between the circumferential quantity and the circumferential induction speed.
4. The method for modeling the propeller based on the large-blade-disc load working condition according to claim 3, wherein the geometric inflow angle of each station is determined according to the incoming flow speed and the induced pitch of the section at r; each station geometric inflow angle is an included angle between an incoming flow and a rotation plane, and specifically comprises the following steps:
using formulas
Determining a geometric inflow angle of each station;
wherein phi is the geometric inflow angle of each station position, V0Is the incoming flow velocity.
5. The method according to claim 4, wherein the determining the relative inflow velocity of each station according to the geometric inflow angle of each station, the circumferential induced velocity of each station and the induced pitch of the section at r comprises:
using formulas
Determining the relative incoming flow speed of each station;
wherein, W is the relative incoming flow speed of each station.
6. The method for modeling the propeller according to claim 4, wherein the initial chord length of each station is determined according to the optimal ring volume distribution and the relative incoming flow speed of each station; and determining the Reynolds number and the Mach number of the airfoil profile at each station according to the initial chord length of each station, and further determining the corresponding favorable attack angle and lift coefficient under the Reynolds number and the Mach number, wherein the method specifically comprises the following steps:
using formulas
Determining the initial chord length of each station;
wherein, b0For the initial chord length of each station, ClIs the initial lift coefficient.
7. The method according to claim 4, wherein the determining the actual chord length according to the lift coefficient and the determining the pitch angle of each station according to the geometric inflow angle and the favorable attack angle of each station specifically comprise:
determining the pitch angle of each station position by using a formula theta as alpha + phi;
where θ is the pitch angle of each station and α is the favored angle of attack.
8. A propeller modeling system based on a large rotor disk load condition, comprising:
the geometric parameter determining module is used for determining design parameters according to the working conditions of the propeller, determining the number of blades of the blades and the radius of the propeller according to the design parameters, and simultaneously determining the airfoil shape of the section which is divided from the hub to the tip of the propeller; the design parameters include: designing height, incoming flow speed, design tension and design angular speed;
the induced pitch determining module is used for determining the induced pitch of the section at the position r according to the number of the blades of the propeller, the radius of the propeller, the design parameters and the design state; the design state includes: the rotation speed and the density;
the optimal circulation distribution and all station positions annular induction speed determining module is used for determining optimal circulation distribution of the position of the hub and the number of the limited blades according to the induction screw pitch of the section at the r position; determining the annular induction speed of each station according to the optimal annular quantity distribution and the quantity of the blades of the paddle;
the geometric inflow angle determining module of each station is used for determining the geometric inflow angle of each station according to the incoming flow speed and the induced screw pitch of the section at the r position; the geometric inflow angle of each station is the included angle between the incoming flow and the rotating plane;
the relative incoming flow velocity determining module of each station is used for determining the relative incoming flow velocity of each station according to the geometric inflow angle of each station, the annular induction velocity of each station and the induction screw pitch of the section at the r position;
the beneficial attack angle and lift coefficient determining module is used for determining the initial chord length of each station according to the optimal circulation distribution and the relative incoming flow speed of each station; determining the Reynolds number and the Mach number of the airfoil profile of each station according to the initial chord length of each station, and further determining the corresponding favorable attack angle and lift coefficient under the Reynolds number and the Mach number;
the actual chord length and each station pitch angle determining module is used for determining the actual chord length according to the lift coefficient and determining each station pitch angle according to the geometric inflow angle and the favorable attack angle of each station;
and the propeller three-dimensional modeling module is used for carrying out propeller three-dimensional modeling according to the airfoil section, the actual chord length and the pitch angle of the section so as to complete propeller blade design.
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| CN117131608A (en) * | 2023-10-23 | 2023-11-28 | 南京航空航天大学 | Excitation disk method based on optimal annular quantity distribution |
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2021
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117131608A (en) * | 2023-10-23 | 2023-11-28 | 南京航空航天大学 | Excitation disk method based on optimal annular quantity distribution |
| CN117131608B (en) * | 2023-10-23 | 2024-03-15 | 南京航空航天大学 | Excitation disk method based on optimal annular quantity distribution |
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