CN115238378B - Aerodynamic design method with large attack angle - Google Patents
Aerodynamic design method with large attack angle Download PDFInfo
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- CN115238378B CN115238378B CN202210822547.4A CN202210822547A CN115238378B CN 115238378 B CN115238378 B CN 115238378B CN 202210822547 A CN202210822547 A CN 202210822547A CN 115238378 B CN115238378 B CN 115238378B
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Abstract
The application belongs to the technical field of aircraft design, and particularly relates to a aerodynamic design method with a large attack angle. The method comprises the following steps of S1, evaluating longitudinal aerodynamic force of an airplane based on CFD simulation, and matching aerodynamic force profiles meeting the requirements of lift force, pitching moment and low radar scattering cross section; s2, performing design and model processing of a plurality of schemes of the shape and the section shape of the aircraft precursor; s3, performing a wind tunnel test, and selecting a precursor plane shape according to the transverse heading characteristic constraint of the aircraft with a large attack angle; and S4, checking and optimizing the profile of the precursor profile on the basis of the selection of the planar shape of the precursor, and selecting the profile of the precursor profile meeting the constraint of the transverse heading characteristic of the aircraft with a large attack angle. The early stage of the method is based on the rapid longitudinal design of an Euler equation and the check analysis of an NS equation, so that the design process is quickened, the multi-scheme design of test variable parameters is carried out on the basis of simulation, the workload of model selection design is remarkably reduced, and the convergence of a large-attack-angle aerodynamic design scheme is quickened.
Description
Technical Field
The application belongs to the technical field of aircraft design, and particularly relates to a aerodynamic design method with a large attack angle.
Background
The aerodynamic design with a large attack angle is an important work of the aerodynamic design of the airplane, and the airplane flight safety is related to the airplane performance and the airplane capability. It relates to longitudinal lift, pitching moment, lateral stability and yaw characteristics. The lift force requirement is longitudinally met, the low head control capability is safely met, the transverse heading meets the transverse heading stability requirement, and the non-instruction rolling moment and the yaw moment of the basic state with a large attack angle meet the safety requirement. Because the large-attack-angle aerodynamic design involves more contents, the large-attack-angle aerodynamic has strong nonlinearity, the linear relation between aerodynamic characteristics and geometric shapes is poor, the aerodynamic design has no systematic method, and in addition, the traditional large-attack-angle aerodynamic design is mainly based on a large number of wind tunnel type selection tests, so the large-attack-angle aerodynamic design is a very complex and time-consuming work, for example, hundreds of precursor strake shapes are experimentally researched in the design process of a certain aircraft, the lift force is improved, the longitudinal and transverse characteristics are matched, and the F-xx and Su-xx type aircraft also develop a large number of strake and precursor type selection designs.
Future aircraft pursue higher functional characteristics, design constraints are enhanced, and at the same time, rapid design and short cycles are required, and it becomes more difficult to design an aircraft that satisfies performance requirements and satisfactory large angle of attack characteristics.
Disclosure of Invention
In order to solve the above problems, the present application provides a aerodynamic design method with a large attack angle, which mainly includes:
step S1, evaluating longitudinal aerodynamic force of an aircraft based on CFD simulation, and matching aerodynamic force profiles meeting the requirements of lift force, pitching moment and low radar cross section;
s2, performing design and model processing of a plurality of schemes of the shape and the section shape of the aircraft precursor;
s3, performing a wind tunnel test, and selecting a precursor plane shape according to the transverse heading characteristic constraint of the aircraft with a large attack angle;
and S4, checking and optimizing the profile of the precursor profile on the basis of the selection of the planar shape of the precursor, and selecting the profile of the precursor profile meeting the constraint of the transverse heading characteristic of the aircraft with a large attack angle.
Preferably, in step S1, the evaluation of the longitudinal aerodynamic force of the aircraft based on CFD simulation comprises:
and calculating a large number of large attack angles for early design selection and optimization through an Euler equation, and checking by adopting an NS equation.
Preferably, in step S1, the evaluation of the longitudinal aerodynamic force of the aircraft based on the CFD simulation comprises:
s11, developing the design of the outline of the back body or the plane of the horizontal tail based on given preliminary precursor outline and low radar cross section constraint, evaluating the lift force and the pitching moment based on a CFD simulation method of an Euler equation, and selecting an outline design scheme of the back body or the plane of the horizontal tail which meets the requirement;
and step S12, designing geometrical parameters of the length, the sweepback angle and the width of the precursor under the constraint of the low radar scattering cross section, evaluating lift force and pitching moment based on an Euler equation through parameter optimization, and matching the appearance of the precursor meeting the requirement.
Preferably, the lateral characteristic constraints of the high angle of attack aircraft include lift and pitch moment constraints.
Preferably, the lateral heading characteristic constraints of the high angle of attack aircraft include lateral and heading stability constraints.
Preferably, the lateral heading characteristic constraint of the high-angle-of-attack aircraft comprises a lateral heading deviation characteristic constraint.
The early stage of the method is based on the rapid longitudinal design of an Euler equation and the check analysis of an NS equation, so that the design process is quickened, the multi-scheme design of test variable parameters is carried out on the basis of simulation, the workload of model selection design is remarkably reduced, and the convergence of a large-attack-angle aerodynamic design scheme is quickened.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of the large angle of attack aerodynamic design method of the present application.
Detailed Description
For the purposes, technical solutions and advantages of the present application, the following describes the technical solutions in the embodiments of the present application in more detail with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The application provides a large attack angle aerodynamic force design method, as shown in fig. 1, mainly comprising the following steps:
step S1, evaluating longitudinal aerodynamic force of an aircraft based on CFD simulation, and matching aerodynamic force profiles meeting the requirements of lift force, pitching moment and low radar cross section;
s2, performing design and model processing of a plurality of schemes of the shape and the section shape of the aircraft precursor;
s3, performing a wind tunnel test, and selecting a precursor plane shape according to the transverse heading characteristic constraint of the aircraft with a large attack angle;
and S4, checking and optimizing the profile of the precursor profile on the basis of the selection of the planar shape of the precursor, and selecting the profile of the precursor profile meeting the constraint of the transverse heading characteristic of the aircraft with a large attack angle.
The large attack angle aerodynamic nonlinearity is strong, the aerodynamic characteristic of the large attack angle aerodynamic nonlinearity depends on the appearance of a precursor, CFD analysis in a middle attack angle and small attack angle range has a good prediction effect, but the large attack angle range transverse heading characteristic is related to separation and symmetry of left and right separation, so that the CFD prediction reliability of the large attack angle transverse heading characteristic is obviously reduced, and the large attack angle transverse heading characteristic analysis mainly depends on wind tunnel tests. Therefore, the longitudinal aerodynamic design is firstly carried out based on the step S1, then the transverse heading design is carried out based on the step S2-step S4, the longitudinal model selection design is carried out based on the Eulter equation simulation rapid CFD technology in the early stage, the variable parameter test model selection research is carried out based on the CFD in the later stage, and the relevant design of the aerodynamic characteristics with a large attack angle is rapidly completed in the scheme model selection design stage.
The step S3 and the step S4 are performed to perform a test model selection design of "the previous body plane shape and then the precursor profile shape", and based on the CFD profile, a multi-scheme design and model processing of the precursor plane shape and the profile shape are performed. And carrying out wind tunnel tests to select the plane shape of the precursor according to the longitudinal lift force characteristic and the pitching moment characteristic. On the basis of which the profile of the precursor profile is checked and preferred, the large angle of attack transverse heading characteristic is confirmed.
In some alternative embodiments, in step S1, evaluating longitudinal aerodynamic forces of the aircraft based on the CFD simulation comprises:
and calculating a large number of large attack angles for early design selection and optimization through an Euler equation, and checking by adopting an NS equation.
The vertical aerodynamic force design evaluation adopts an Eulter equation with small calculation amount to quickly evaluate, the Eulter equation can generally reflect the flow separation development trend although ignoring viscosity, partially simulate separation vortex, seriously separate flow under a large attack angle, calculate convergence difference, aerodynamic force fluctuates at a certain amplitude value, take an average value, and have higher reference significance in layout analysis according to experience, so that the calculation of a large amount of large attack angles with early design selection and optimization can be evaluated by adopting the Eulter equation, design references can be adjusted by a scheme, an acceleration scheme is iteratively designed, and verification analysis can be performed by using NS before wind tunnel test.
In some alternative embodiments, in step S1, evaluating longitudinal aerodynamic forces of the aircraft based on the CFD simulation comprises:
s11, developing the design of the outline of the back body or the plane of the horizontal tail based on given preliminary precursor outline and low radar cross section constraint, evaluating the lift force and the pitching moment based on a CFD simulation method of an Euler equation, and selecting an outline design scheme of the back body or the plane of the horizontal tail which meets the requirement;
and step S12, designing geometrical parameters of the length, the sweepback angle and the width of the precursor under the constraint of the low radar scattering cross section, evaluating lift force and pitching moment based on an Euler equation through parameter optimization, and matching the appearance of the precursor meeting the requirement.
The embodiment adopts a large-attack-angle longitudinal simulation design of 'sequential body/horizontal tail re-matched precursor/strake', and the large-attack-angle longitudinal characteristic is related to the external dimensions of the precursor/strake and the rear body/horizontal tail of the airplane except for a main wing. Excessive precursors bring high head-up moment, require large aft-body/tail, but large tail and aft-body bring high drag and weight costs. Therefore, the parameters of the back body/tail wing and the resistance are selected by combining engineering experience, the design of the plane shape of the back body/tail wing is developed under the constraints of the initial front body shape and the low radar scattering cross section, the lift force and the pitching moment are estimated by a CFD simulation method based on an Euler equation, and a back body/tail wing scheme is optimized. Under the condition that the back body scheme is basically determined, the plane shape of the front body/edge strip is matched, under the constraint of a low radar scattering cross section, geometrical parameters such as the length of the front body, the sweepback angle, the width of the front body and the like are designed, lift force and pitching moment are evaluated by a rapid evaluation method based on an Euler equation through parameter optimization, and the shape of the front body is matched.
Step S3 and step S4 are performed by the trial selection design of "previous body plan shape followed by precursor profile shape
In some alternative embodiments, the yaw characteristic constraints of the high angle of attack aircraft include lift and pitch moment constraints.
In some alternative embodiments, the yaw characteristic constraints of the high angle of attack aircraft include yaw and yaw stability constraints.
In some alternative embodiments, the lateral heading characteristic constraint of the high-angle-of-attack aircraft includes a lateral-heading-deviation characteristic constraint.
The early stage of the method is based on the rapid longitudinal design of an Euler equation and the check analysis of an NS equation, so that the design process is quickened, the multi-scheme design of test variable parameters is carried out on the basis of simulation, the workload of model selection design is remarkably reduced, and the convergence of a large-attack-angle aerodynamic design scheme is quickened.
While the application has been described in detail with respect to the general description and the specific embodiments thereof, it will be apparent to those skilled in the art that certain modifications and improvements can be made thereto based upon the application. Accordingly, such modifications or improvements may be made without departing from the spirit of the application and are intended to be within the scope of the invention as claimed.
Claims (4)
1. A method of aerodynamic design with a large angle of attack, comprising:
step S1, evaluating longitudinal aerodynamic force of an aircraft based on CFD simulation, and matching aerodynamic force profiles meeting the requirements of lift force, pitching moment and low radar cross section;
s2, performing design and model processing of a plurality of schemes of the shape and the section shape of the aircraft precursor;
s3, performing a wind tunnel test, and selecting a precursor plane shape according to the transverse heading characteristic constraint of the aircraft with a large attack angle;
s4, checking and optimizing the profile of the precursor profile on the basis of the plane shape selection of the precursor, and selecting the profile of the precursor profile meeting the constraint of the transverse heading characteristic of the aircraft with a large attack angle;
in step S1, the evaluation of the longitudinal aerodynamic force of the aircraft based on the CFD simulation includes:
calculating a large number of large attack angles for early design selection and optimization through an Euler equation, and checking by adopting an NS equation;
in step S1, evaluating longitudinal aerodynamic forces of an aircraft based on CFD simulation includes:
s11, developing the design of the outline of the back body or the plane of the horizontal tail based on given preliminary precursor outline and low radar cross section constraint, evaluating the lift force and the pitching moment based on a CFD simulation method of an Euler equation, and selecting an outline design scheme of the back body or the plane of the horizontal tail which meets the requirement;
and step S12, designing geometrical parameters of the length, the sweepback angle and the width of the precursor under the constraint of the low radar scattering cross section, evaluating lift force and pitching moment based on an Euler equation through parameter optimization, and matching the appearance of the precursor meeting the requirement.
2. The high angle of attack aerodynamic design method of claim 1 wherein the lateral characteristic constraints of the high angle of attack aircraft include lift and pitch moment constraints.
3. The high angle of attack aerodynamic design method of claim 1 wherein the high angle of attack aircraft lateral heading characteristic constraints include lateral and heading stability constraints.
4. The high angle of attack aerodynamic design method of claim 1, wherein the high angle of attack aircraft lateral heading characteristic constraints include lateral heading deviation characteristic constraints.
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| RU2695897C1 (en) * | 2018-10-26 | 2019-07-29 | Акционерное общество "Лётно-исследовательский институт имени М.М. Громова" | Method and system for controlling longitudinal movement during takeoff on flight strip and climbing of unmanned aerial vehicle with specially arranged front and rear wings |
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| US8442705B2 (en) * | 2009-02-27 | 2013-05-14 | Airbus Operations Gmbh | Method and device for determining aerodynamic characteristics of an aircraft |
| ITTO20110122A1 (en) * | 2011-02-14 | 2012-08-15 | Alenia Aermacchi Spa | AIRCRAFT CONFIGURATION TO IMPROVED AERODYNAMIC PERFORMANCES. |
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| RU2695897C1 (en) * | 2018-10-26 | 2019-07-29 | Акционерное общество "Лётно-исследовательский институт имени М.М. Громова" | Method and system for controlling longitudinal movement during takeoff on flight strip and climbing of unmanned aerial vehicle with specially arranged front and rear wings |
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