CN109540459B - Pneumatic characteristic numerical calculation result correction method - Google Patents
Pneumatic characteristic numerical calculation result correction method Download PDFInfo
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- CN109540459B CN109540459B CN201811333267.7A CN201811333267A CN109540459B CN 109540459 B CN109540459 B CN 109540459B CN 201811333267 A CN201811333267 A CN 201811333267A CN 109540459 B CN109540459 B CN 109540459B
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Abstract
The application provides a pneumatic characteristic numerical result correction method, which belongs to the technical field of helicopter tests, obtains a correction coefficient of a pneumatic characteristic CFD calculated value by obtaining an existing helicopter pneumatic characteristic wind tunnel test value and a CFD calculated value which are similar to a target helicopter pneumatic structure, and obtains the pneumatic characteristic CFD calculated value of the target helicopter through the correction coefficient. Compared with a method for obtaining the aerodynamic characteristic value through a wind tunnel test, the aerodynamic characteristic value result correction method can shorten the design time by 70%, can reduce the cost, and provides an effective and feasible method for rapid design and cost reduction of the helicopter.
Description
Technical Field
The application belongs to the technical field of helicopter tests, and particularly relates to a pneumatic characteristic numerical calculation result correction method.
Background
In the process of developing the helicopter, the aerodynamic characteristics of the fuselage and each component are important basic data, and are the basis for calculating the flight performance, flight quality, flight load, rotor load and the like of the helicopter, so that more accurate aerodynamic characteristic data need to be obtained.
In the prior helicopter development process, a wind tunnel test method is usually adopted to obtain aerodynamic characteristic data of a newly developed helicopter type. The wind tunnel test usually takes a relatively long time to design and manufacture the test model, and meanwhile, the test time arrangement of the wind tunnel needs to be waited. The optimal design scheme of the helicopter appearance or a certain part cannot be verified quickly in the wind tunnel test process, and the verification can be realized only when waiting for the next wind tunnel test.
Disclosure of Invention
The present application is directed to a method for correcting a result of a calculation of a pneumatic characteristic value, so as to solve any one of the above problems.
The technical scheme of the application is as follows: a method of correcting a result of a numerical calculation of an aerodynamic characteristic, the method comprising: the method comprises the following steps: acquiring aerodynamic characteristic data of an existing helicopter wind tunnel test with the same configuration as a target helicopter; step two: calculating aerodynamic characteristic data of the existing helicopter according to a CFD method; step three: comparing the aerodynamic characteristic data of the existing helicopter wind tunnel test with the aerodynamic characteristic data of the CFD method, and if the aerodynamic characteristic data of the existing helicopter wind tunnel test and the aerodynamic characteristic data of the CFD method have different variation trends, adjusting the CFD method in the step two to enable the aerodynamic characteristic data of the existing helicopter wind tunnel test and the aerodynamic characteristic data of the CFD method to have the same variation trend; step four: obtaining a correction coefficient according to the aerodynamic characteristic data of the wind tunnel test of the existing helicopter and the aerodynamic characteristic data of the CFD method; step five: calculating aerodynamic characteristic data of the target helicopter according to the CFD method; step six: and acquiring wind tunnel test simulation aerodynamic characteristic data of the target helicopter according to the aerodynamic characteristic data of the target helicopter and the correction coefficient.
In an embodiment of the application, in step one, the aerodynamic characteristic data includes drag, lift, lateral force, roll torque, pitch torque, and yaw torque.
In an embodiment of the present application, in step four, the correction coefficients are: and the ratio of the aerodynamic characteristic data obtained by the wind tunnel test of the existing helicopter to the aerodynamic characteristic data obtained by the CFD method.
In an embodiment of the present application, in step four, the correction coefficients are: and the ratio of the aerodynamic characteristic data obtained by the CFD method to the aerodynamic characteristic data obtained by the wind tunnel test of the existing helicopter.
In an embodiment of the present application, obtaining the correction coefficient further includes: obtaining a plurality of groups of correction coefficients; and acquiring the required correction coefficient in the plurality of groups of correction coefficients according to a preset rule.
In an embodiment of the present application, the predetermined rule includes an average method, a mode method, or a median method.
In an embodiment of the application, in step six, the method for obtaining the wind tunnel test simulated aerodynamic characteristic data of the target helicopter includes: and performing one or more of product operation on the aerodynamic characteristic data of the target helicopter and the correction coefficient and power operation on the aerodynamic characteristic data of the target helicopter and the correction coefficient.
In an embodiment of the present application, in step three, the CFD method is adjusted so that a variation trend of aerodynamic characteristic data of an existing helicopter wind tunnel test is the same as a variation trend of aerodynamic characteristic data of the CFD method, and the method includes: and adjusting one or more of meshing, turbulence mode and boundary condition in the CFD method.
Compared with a wind tunnel test method, the aerodynamic characteristic numerical calculation result correction method can shorten the design time by 70%, can reduce the cost, and provides an effective and feasible method for rapid design and cost reduction of the helicopter. The method effectively combines the previous wind tunnel test data with a mature CFD calculation method, and can quickly obtain the aerodynamic characteristic data of a newly-developed model, so that the method is an effective support for accelerating the development progress of the model of the helicopter and reducing the development cost.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a flow chart of the present application.
FIG. 2 is a schematic diagram of drag coefficients according to an embodiment of the present application.
Fig. 3 is a schematic view of a pitching moment according to an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to solve the problems that in the prior art, the aerodynamic characteristic data can only be obtained through a wind tunnel test in the research and development process of the helicopter, and cannot be verified quickly after the aerodynamic characteristic data is modified, the application provides a method for correcting the calculation result of the aerodynamic characteristic value, and the accurate aerodynamic characteristic data of a newly-developed helicopter (hereinafter referred to as a target helicopter) can be obtained quickly.
The method for correcting the calculation result of the aerodynamic characteristic value comprises the following steps:
firstly, selecting wind tunnel test data and aerodynamic shape of an existing helicopter type similar to the aerodynamic shape of a target helicopter according to the characteristics of the fuselage shape, the hub shape, the undercarriage configuration, the tail aerodynamic surface and the like of the target helicopter.
In the present application, the above-mentioned aerodynamic characteristic data includes drag, lift, lateral force, roll moment, pitch moment, yaw moment, and the like.
Second, the aerodynamic characteristics of the selected existing helicopter are calculated using the CFD (Computational Fluid Dynamics) method. In the numerical calculation process, the incoming flow speed in the CFD calculation is the same as the wind tunnel test condition of the existing helicopter, and the aerodynamic shape of the calculation model is kept the same as far as possible as the wind tunnel test model.
And thirdly, comparing and analyzing the aerodynamic characteristic data obtained by CFD calculation with the wind tunnel test value of the existing helicopter, verifying the accuracy and reliability of the CFD calculation method, and if the aerodynamic characteristic data and the wind tunnel test value are not consistent, adjusting the grid division, turbulence mode and the like in the CFD method in the second step until the variation trends of the two are the same.
And fourthly, comparing aerodynamic characteristic parameters of wind tunnel test values of the existing helicopter with aerodynamic parameters of resistance, lift force, lateral force, rolling moment, pitching moment, yawing moment and the like obtained by a CFD method, and selecting a correction coefficient by comprehensively considering factors of all aspects.
In the process of selecting the correction coefficient, the required correction coefficient can be obtained according to the ratio of the aerodynamic characteristic data of the existing helicopter wind tunnel test to the aerodynamic characteristic data of the CFD method, or the required correction coefficient can be obtained according to the ratio of the aerodynamic characteristic data of the CFD method to the aerodynamic characteristic data of the existing helicopter wind tunnel test.
In addition, in the present application, if there are a plurality of correction coefficients, a more accurate correction coefficient may be obtained according to a certain rule, where the certain rule may be a method of taking an average value, a median value, or a mode.
For example, in the embodiment shown in fig. 2, the attack angle is in the range of-12 ° to +12 °, the resistance coefficient is a first-order curve, the resistance coefficient curve is far from the origin, the correction coefficients obtained by the ratio of the aerodynamic characteristic data of the wind tunnel test and the aerodynamic characteristic data obtained by the CFD method are 1.7, 1.6, 1.5, 1.62 and 1.71 in sequence, and the correction coefficient is selected to be the middle value 1.6 in the correction coefficient group through comprehensive evaluation.
For another example, in another embodiment shown in fig. 3, the angle of attack is in the range of-12 ° - +12 degrees, the pitch moment is linear, the pitch moment curve passes through the origin, and the correction coefficients obtained from the ratio of the aerodynamic characteristic data of the wind tunnel test and the aerodynamic characteristic data obtained by the CFD method are 1.2, 1.25, 1.31, 10, 15, 12, 1.35, and 1.24 in this order. Because the ratio of the aerodynamic characteristic data of the wind tunnel test to the aerodynamic characteristic data obtained by the CFD method is far larger than other parts at a small angle (near the origin), the reliability of the ratio near the small angle is very low, and in the embodiment, the correction coefficient takes the middle value of the ratio which is not in the small angle range to be 1.25.
And fifthly, performing aerodynamic characteristic calculation on the target helicopter by adopting the same CFD method, wherein the mesh division, the turbulence mode selection in the calculation process, the boundary condition setting and the like in the CFD method are the same as those in the prior art.
And sixthly, correcting the pneumatic characteristic CFD value of the target helicopter through the correction coefficient obtained in the step four to obtain the pneumatic characteristic data of the target helicopter.
Finally, the target helicopter can be subjected to index inspection such as resistance according to the corrected aerodynamic characteristic data of the target helicopter, and if the aerodynamic characteristic data of the target helicopter does not meet the relevant indexes, the shape of the helicopter body and the parts can be optimally designed.
The aerodynamic characteristic numerical value calculation result correction method can rapidly obtain the aerodynamic characteristic data of the target helicopter, and provides calculation basic data for calculation and evaluation of the next flight performance, flight quality, flight load, rotor load and the like of the helicopter. Compared with a wind tunnel test method, the aerodynamic characteristic numerical calculation result correction method can shorten the design time by 70% and reduce the cost.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A method for correcting a calculation result of a pneumatic characteristic value is characterized by comprising the following steps
The method comprises the following steps: acquiring aerodynamic characteristic data of an existing helicopter wind tunnel test with the same configuration as a target helicopter;
step two: calculating aerodynamic characteristic data of the existing helicopter according to a CFD method;
step three: comparing the aerodynamic characteristic data of the existing helicopter wind tunnel test with the aerodynamic characteristic data of the CFD method, and if the aerodynamic characteristic data of the existing helicopter wind tunnel test and the aerodynamic characteristic data of the CFD method have different variation trends, adjusting the CFD method in the step two to enable the aerodynamic characteristic data of the existing helicopter wind tunnel test and the aerodynamic characteristic data of the CFD method to have the same variation trend;
step four: obtaining a correction coefficient according to the aerodynamic characteristic data of the wind tunnel test of the existing helicopter and the aerodynamic characteristic data of the CFD method;
step five: calculating aerodynamic characteristic data of the target helicopter according to the CFD method;
step six: and acquiring wind tunnel test simulation aerodynamic characteristic data of the target helicopter according to the aerodynamic characteristic data of the target helicopter and the correction coefficient.
2. The method for correcting the result of numerical calculation of aerodynamic characteristics according to claim 1, wherein in the first step, the aerodynamic characteristic data includes drag, lift, lateral force, roll moment, pitch moment, and yaw moment.
3. The aerodynamic characteristic value calculation result correction method according to claim 1, wherein in the fourth step, the correction coefficient is: and the ratio of the aerodynamic characteristic data obtained by the wind tunnel test of the existing helicopter to the aerodynamic characteristic data obtained by the CFD method.
4. The aerodynamic characteristic value calculation result correction method according to claim 1, wherein in the fourth step, the correction coefficient is: and the ratio of the aerodynamic characteristic data obtained by the CFD method to the aerodynamic characteristic data obtained by the wind tunnel test of the existing helicopter.
5. The aerodynamic characteristic value calculation result modification method according to claim 3 or 4, wherein obtaining the modification coefficient further comprises
Obtaining a plurality of groups of correction coefficients;
and acquiring the required correction coefficient in the plurality of groups of correction coefficients according to a preset rule.
6. The aerodynamic characteristic value calculation result modification method according to claim 5, wherein the predetermined rule includes an average method, a mode method, or a median method.
7. The method for correcting the aerodynamic characteristic numerical calculation result according to claim 1, wherein in step six, the method for obtaining the wind tunnel test simulation aerodynamic characteristic data of the target helicopter comprises: and performing one or more of product operation on the aerodynamic characteristic data of the target helicopter and the correction coefficient and power operation on the aerodynamic characteristic data of the target helicopter and the correction coefficient.
8. The method for correcting the result of calculation of aerodynamic characteristic values according to claim 1, wherein in step three, the CFD method is adjusted so that the aerodynamic characteristic data of the wind tunnel test of the existing helicopter has the same trend of change as the aerodynamic characteristic data of the CFD method, including
And adjusting one or more of meshing, turbulence mode and boundary condition in the CFD method.
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| CN112393876B (en) * | 2019-08-16 | 2022-04-12 | 北京空天技术研究所 | Dynamic pneumatic derivative prediction method suitable for internal and external flow integrated appearance |
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| CN112163381A (en) * | 2020-09-25 | 2021-01-01 | 西安热工研究院有限公司 | Lateral boundary condition setting method suitable for complex terrain wind field flow numerical simulation |
| CN112903237B (en) * | 2021-01-22 | 2021-09-28 | 西北工业大学 | POD-based unsteady hole wall interference correction method |
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