KR101612506B1 - System and method for Aircraft areodynamic analysis using CFD - Google Patents

Abstract

The present invention relates to an aerodynamic aircraft analysis system and method using computational fluid dynamics (CFD) based on an open source. More particularly, the present invention relates to an aerodynamic aircraft analysis system using CFD based on an open source which provides a graphic user interface (GUI) so that aerodynamic analysis outside an aircraft is performed using the open source. The system comprises: a pre-processing unit (100) which performs space partition in a grid or mesh form so that a micro volume on an aircraft surface and space is obtained using a provided open source; an aerodynamic solver unit (200) which analyzes aerodynamics generated outside an aircraft using CFD based on the provided open source; and a post-processing unit (300) which processes aerodynamic analysis data received from the aerodynamic solver unit (200) using the provided open source.

Description

Technical Field [0001] The present invention relates to an aircraft aerodynamic analysis system and method using computational fluid dynamics,

The present invention relates to an aircraft aerodynamic analysis system and method using an open source based computational fluid dynamics, and more particularly, to a system and method for analyzing an aerodynamic aerodynamic force using an open source (Open Foam) based computational fluid dynamics (CFD) The present invention relates to an aircraft aerodynamic analysis system and method using an open source based computational fluid dynamics capable of overcoming a cost limitation due to the use of an aircraft and providing an aircraft aerodynamic analysis system and method suitable for an administrator (user).

Over the past 20 years, many aircraft development tasks have been carried out in Korea. After the development of the T-50, challenges such as the development of the Suronon, KC-100, and mid-range civilian navigation were carried out within a short time, and future developments are expected.

Computational Fluid Dynamics (CFD) is increasingly used in the aerodynamic analysis part of several aircraft development periods.

Recently, the field of computational fluid analysis has become prominent even in Korea Aerospace Industries (KAI). Analysis of server computation time in terms of utilization rate of CFD showed that it increased by about 600 more than 5 years ago and that the computation time per problem increased about 200% Due to the nature of the industry, which relies heavily on commercial programs, there is a growing concern about the cost increase problem.

It is expected that the cost portion of commercial programs will increase more rapidly than the increase of calculation server and interpretation work in the next 10 years. As an alternative to this commercial program, in case of in-house code, an aerodynamic analysis solver, It can be advantageous in terms of improving the accuracy and has an advantage of being easily modified by the developer.

However, there is a disadvantage in that the advantages of the in-house code in the adaptability and convenience of the CFD engineer for industrial use are reduced.

In other words, CFD engineers in general industry are highly dependent on commercially available programs that can complete complex geometries in a short time. In these commercial programs, advantages such as stability, high parallel performance and user friendliness However, there is a disadvantage that a lot of costs are incurred for quick analysis.

In addition, commercial programs featuring general versatility have a disadvantage in that they are limited in customized development suited to the user environment,

Due to the external temporal integration method, the time required for analysis is relatively increased. In addition to the increase in time and inefficiency of a series of preprocessing operations from complicated aircraft surface geometry to the generation of grids, inefficient work order and errors There is a problem of increase in generation.

Accordingly, the system and method for analyzing aircraft aerodynamic force using the open-source computational fluid dynamics of the present invention can derive a certain level of calculation results in a short period of time, To an aerodynamic analysis system and method.

In Korean Patent No. 10-0993297 ("Method of preprocessing panel code using CATIA ", hereinafter referred to as Prior Art 1), in interpreting data by using a panel code as a flight aerodynamic analysis program, data pre- The panel code preprocessing method using CATIA which makes data interpretation easier and quicker.

Korean Registered Patent No. 10-0993297 (registered on Nov. 23, 2010)

SUMMARY OF THE INVENTION The present invention has been made in order to solve the problems of the conventional art as described above, and it is an object of the present invention to provide a method and apparatus for using a CFD (Computational Fluid Dynamics) The present invention provides an aircraft aerodynamic analysis system and method using an open source based computational fluid dynamics capable of overcoming cost limitations by an operator and providing an aircraft aerodynamic analysis system and method suitable for an administrator (user).

The airborne aerodynamic analysis system using an open source based computational fluid dynamics according to an embodiment of the present invention provides a GUI (Graphic User Interface) to perform an aerodynamic analysis of an aircraft using an open source (Open Foam) In an aircraft aerodynamic analysis system using an open source based computational fluid dynamics, space division is performed in the form of a grid or a mesh so as to have a small volume on the surface and space of the aircraft using the open source provided A preprocessing unit 100, an aerodynamic solver unit 200 for analyzing an aerodynamic force generated on the outside of the aircraft using computational fluid dynamics (CFD) based on the open source provided, And a post-processing unit (300) for processing the aerodynamic analysis data transmitted from the aerodynamic analysis unit (200) using a source All.

Further, the preprocessing unit 100 inputs the size of the calculation area, the grid size around the aircraft, the height and number of the boundary layer as input variables of the open source, generates a hexahedral grid around the aircraft, Is converted into a polyhedron by matching the shape of the aircraft with the shape of the aircraft, and the boundary-side lattice is generated to perform spatial division.

Also, the aerodynamic analysis unit 200 inputs the type of the boundary surface, the range of machinability, the range of the angle of attack (AOA), the pressure and the temperature of the far boundary as input variables of the open source, And the analysis of the aerodynamic force generated on the outside of the aircraft through the intrinsic time integration method and the turbulence model analysis.

The post-processing unit 300 inputs the aerodynamic analysis data received from the aerodynamic analysis unit 200 as input variables of the open source to be provided. The post-processing unit 300 receives the aerodynamic force data CL, (Lift Coefficient), a drag coefficient (CD), and a moment coefficient (CM).

A method of analyzing an aerodynamic aerodynamic force using computational fluid dynamics based on open source according to an embodiment of the present invention provides a graphical user interface (GUI) for performing an aerodynamic analysis of an aircraft using an open source (Open Foam) A method of analyzing an aerodynamic aerodynamic force using an open source based computational fluid dynamics, the method comprising: performing spatial division in a grid or mesh shape so as to have a small volume on the surface and space of an aircraft using the open source provided; A preprocessing step (S100), an aerodynamic analysis step (S200) for analyzing an aerodynamic force generated on the outside of the aircraft using CFD (Computational Fluid Dynamics) based on the open source provided, , Aerodynamic analysis data by the aerodynamic analysis step (S200) is received and processed as data of graph or graphic form, It characterized by comprising the step (S300).

In this case, the preprocessing step S100 inputs the size of the calculation area, the grid size around the aircraft, the height and number of the boundary layer as input variables of the open source to be input, generates a hexahedral grid around the aircraft, Is converted into a polyhedron by matching the shape of the airplane with the shape of the aircraft, and space division is performed by generating the boundary-side lattice,

The aerodynamic analysis step S200 inputs the type of the boundary surface, the range of Mach number, the range of the angle of attack (AOA), the pressure and the temperature of the far boundary as input variables of the open source, It is characterized by analyzing the aerodynamic force generated on the outside of the aircraft through integration method and turbulence model analysis.

In addition, the post-processing step (S300) inputs the aerodynamic analysis data received from the aerodynamic analysis step (S200) as input variables of the open source to be provided. The force and moment at the aircraft and each interface and the lift coefficient (CL), a lift coefficient (CD), a moment coefficient (CM) and a moment coefficient (CM).

According to an embodiment of the present invention, there is provided a computer-readable recording medium storing a program for implementing an aerodynamic aerodynamic analysis method using the open-source based computational fluid dynamics.

According to another embodiment of the present invention, there is provided a computer program created by a command for implementing an aircraft aerodynamic analysis method using the open-source based computational fluid dynamics.

The system and method for analyzing aircraft aerodynamic force using the open-source computational fluid dynamics of the present invention having the above-described structure can be implemented by using an Open Foam-based computational fluid dynamics (CFD) By overcoming the cost limit by use and providing an aircraft aerodynamic analysis system and method suitable for an administrator (user)

A graphical user interface (GUI) that reflects the needs of the phenomenon, and the time required for interpretation work, is provided by the LU-SHS numerical model for the aerodynamic analysis (solver, solver) It has the effect of optimizing the customized grid automation function for development, developing the graphical user interface for it, and improving the efficiency of the system by developing the customized postprocessing function.

For this purpose, the development code was verified to be accurate in various conditions to avoid problems when used in the aircraft design analysis process. It is possible to improve the efficiency of analysis work.

In addition, the airborne aerodynamic analysis system and method using the open-source computational fluid dynamics of the present invention can develop a simple user environment, that is, a graphical user interface, so that anyone can easily use the system, And,

By optimizing many input conditions and automating tasks, it is possible to improve the efficiency of research and development by minimizing the amount of time that developers spend on aerodynamic analysis.

That is, the aircraft aerodynamic analysis system and method using the open-source computational fluid dynamics of the present invention can solve the aerodynamic analysis by solving the aerodynamic solving method by applying the implicit time integration method to obtain the analysis time required 3 to 5 times faster than the external temporal integration method Can be shortened,

By integrating a series of preprocessing operations from complex aircraft surface geometry to grid generation into semi-automatic concepts, it is possible to shorten work time effectively,

It is possible to simplify the post-processing repetitive work of a large capacity and to increase the work efficiency and reduce the possibility of errors.

FIG. 1 is a block diagram illustrating an aircraft aerodynamic analysis system using an open source based computational fluid dynamics according to an exemplary embodiment of the present invention. Referring to FIG.
2 is a graphical representation of a GUI provided by the preprocessing unit 100 of an aircraft aerodynamic analysis system using computational fluid dynamics based on open source according to an embodiment of the present invention.
FIG. 3 through FIG. 6 are graphical examples of graphical results of an aerodynamic analysis result of an aerodynamic analysis unit 200 of an aircraft aerodynamic analysis system using an open-source computational fluid dynamics according to an embodiment of the present invention.
7 is a graphical representation of a GUI provided by a post-processing unit 300 of an aircraft aerodynamic analysis system using computational fluid dynamics based on open source according to an embodiment of the present invention.
FIG. 8 is a flowchart illustrating an aerodynamic aerodynamic analysis method using an open-source computational fluid dynamics according to an embodiment of the present invention.

Hereinafter, an airborne aerodynamic analysis system and method using an open source based computational fluid dynamics according to an embodiment of the present invention will be described in detail with reference to the accompanying drawings. The following drawings are provided by way of example so that those skilled in the art can fully understand the spirit of the present invention. Therefore, the present invention is not limited to the following drawings, but may be embodied in other forms. In addition, like reference numerals designate like elements throughout the specification.

In this case, unless otherwise defined, technical terms and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. In the following description and the accompanying drawings, A description of known functions and configurations that may unnecessarily obscure the description of the present invention will be omitted.

A system and method for analyzing an aircraft aerodynamic force using an open-source computational fluid dynamics of the present invention includes a system and a system for providing a graphical user interface (GUI) for performing an aerodynamic analysis of an aircraft using an open source (Open FOAM) Interpretation method. The open form is a toolbox for the development of computational fluid dynamics code. It consists of a lattice processing, a matrix calculator, and a matrix calculator. It is based on Open FOAM, an unstructured grid analysis code using finite volume method of open source. Boundary conditions, and turbulence models.

The open-form aerodynamic analysis (solver) for the currently available compressible flow analysis uses the SIMPLE algorithm and the external method.

Since they have limitations for efficient aerodynamic analysis, the airborne aerodynamic analysis system and the method using the open-source computational fluid dynamics of the present invention have developed a compressible code employing an internal method using the LU-SGS numerical model, The efficiency can be increased.

1 is a diagram illustrating an aircraft aerodynamic analysis system using computational fluid dynamics based on open source according to an embodiment of the present invention. Referring to FIG. 1, an aircraft aerodynamic analysis system using an open-source computational fluid dynamics of the present invention will be described in detail.

1, an airborne aerodynamic analysis system using an open-source based computational fluid dynamics according to an embodiment of the present invention includes a pre-processing unit 100, an aerodynamic analysis unit 200, and a post-processing unit 300 .

To learn more about each configuration,

As shown in FIG. 2, the preprocessing unit 100 uses a provided open source to perform spatial division in a grid-like or mesh-like shape so as to have a small volume on the surface of the aircraft and the space outside the aircraft Can be performed.

As an open source provided to the preprocessing unit 100, snappy Hex Mesh, which is a grid generation utility provided by OpenForm, is used, but this is only an embodiment of the present invention.

Specifically, the preprocessing unit 100 includes a castellate process for creating a hexagonal lattice in an outer space of an aircraft using an STL file of an aircraft shape, a snap process for converting the hexagonal lattice into a polyhedral lattice by matching the shape of the aircraft, A grid is generated directly from the shape file through the process of generating the grid.

The process of creating a feature line from a file is added, and the grid generation process is performed by using the size of the calculation area, the grid size around the aircraft, the height and number of the boundary layer, etc. It is possible to create a grid with only a few input variables, and it is possible to work in parallel, which is a grid generation method that is very easy to generate an automatic grid.

In the aircraft aerodynamic analysis system using the open-source computational fluid dynamics of the present invention, the influence of about 60 kinds of input values was tested to determine the optimum condition, and most parameters were fixed, .

That is, in other words, the preprocessing unit 100 generates a hexahedral grid around the aircraft by inputting the size of the calculation area, the grid size around the aircraft, the height and number of the boundary layer, The grid can be converted into a polyhedral grid by matching with the shape of the aircraft, and the space division can be performed by generating the boundary grid. In this case, the numerical model was set only by the turbulence model, the discretization technique, and the constraint. The boundary condition was the Riemann condition, and the wall condition according to the y + value was automatically set on the surface of the aircraft have.

The aerodynamic solver 200 can analyze an aerodynamic force generated outside the aircraft using computational fluid dynamics (CFD) based on the open source provided.

The aerodynamic analysis unit 200 inputs the type of the boundary surface, the range of machinability, the range of the angle of attack (AOA), the pressure and temperature value of the remote boundary as input variables, and inputs the same into the open source.

Through this, intrinsic time integral method and turbulence model analysis can easily analyze the aerodynamic force generated from the outside of the aircraft.

In detail, Riemann boundary condition, intrinsic time integration method based on unstructured grid (LU-SGS), automatic wall function numerical code for wall boundary condition of turbulence model are additionally performed And includes a turbulence model for transition prediction in compressible flow.

FIG. 3 is a flow chart showing the results of simulation of a three-dimensional transonic blade analysis result using a commercial program (commercial CFD S / W Fluent) and the present invention (ISAAC Of the aerodynamic force analysis unit 200 of the aerodynamic analysis unit 200 shown in FIG.

The aerodynamic analysis unit 200 performs calculation for checking the remote boundary condition, constraint, convergence, and solution accuracy of the development code using ONERA M6 wing, which is a three-dimensional shape and a lattice shape, Respectively,

The turbulence model is based on the k-ω SST model, and the angle of attack is 3.06 degrees and the Mach number is 0.84.

In addition, the pressure distribution in the ONERA M6 wing analysis results is shown in Fig.

As shown in FIGS. 3 and 4, the overall surface pressure distribution shows well the flapper analysis results and the analysis results of the present invention (ISAAC) The results are comparable.

5 to 6 illustrate a commercial program (commercial CFD S / W Fluent) for the three-dimensional aircraft shape problem in the aerodynamic analysis unit 600 of the aircraft aerodynamic analysis system using the open-source computational fluid dynamics of the present invention 1 is a diagram illustrating an aerodynamic analysis result of the present invention (ISAAC).

The aerodynamic analysis unit 600 performs calculation for confirming the remote boundary condition, constraint, convergence and solution accuracy of the development code using the three-dimensional aircraft shape DLR-F6, and derives the result as shown in FIG. 5 Respectively.

The total number of gratings is 5 million, and y + is applied to 1 or less. For the turbulence model, the k-ω SST model is used. The angle of attack is 0.49 degrees and the Mach number is 0.74.

As shown in FIGS. 5 to 6, the calculation results of Fluent, which is a commercial program, and the calculation results of the aerodynamic analysis unit 200 (ISAAC) of the present invention all show a similar pressure distribution, The distribution also shows similar results.

The post-processing unit 300 may process the aerodynamic analysis data transmitted from the aerodynamic analysis unit 200 using the open source provided.

The post-processing unit 300 inputs the aerodynamic analysis data received from the aerodynamic analysis unit 200 as input variables such as paraview, fieldview, and tecplot, which are open sources, and calculates the forces and moments at the aircraft and each interface, The lift coefficient (CL), the drag coefficient (CD), and the moment coefficient (CM) can be extracted and output.

In addition, as shown in FIG. 7, the GUI environment can be provided.

In detail, the post-processing unit 300 extracts necessary data using the aerodynamic analysis data calculated by the aerodynamic analysis unit 200.

Since the post-processing operation consumes much time for data conversion, extraction of necessary data, and sorting of various data using a spreadsheet program, in order to minimize this, a GUI Environment,

Force and moment at all aircraft and each interface and lift, drag, and moment coefficients are automatically extracted, and graphs of both sexes and drag coefficients according to the angle of attack can be calculated for all Mach numbers .

In addition, when the aircraft span direction coordinate is input, a pressure distribution graph and a data file are generated on the cross section, and the residual value and the resistance coefficient change state during the calculation for the problem are calculated according to the user's request Or can be checked quickly after calculation.

In addition, the GUI of the aircraft aerodynamic analysis system using the open-source computational fluid dynamics of the present invention is constructed so as to be as simple as possible, and is constructed in consideration of the extensibility for future addition of functions.

In other words, the input data necessary for aerodynamic analysis can be computed by using simulation conditions (Mach number, angles of attack, turbulence model, remote boundary condition, etc.), grid (grid file, interface properties), numerical model (discretization technique, matrix calculator, (Aerodynamic data, graph, graphical output, etc.), which are classified into various categories such as conditions (parallel operation, number of iteration, number of CFL, etc.)

As shown in FIG. 7, simulation conditions are arranged on the main screen, and the remaining four categories are constructed as separate input windows.

FIG. 8 is a flowchart illustrating an aerodynamic analysis method using an open-source computational fluid dynamics of the present invention. Referring to FIG. 8, an aircraft aerodynamic analysis method using an open-source computational fluid dynamics of the present invention will be described in detail.

An aircraft aerodynamic analysis method using an open-source computational fluid dynamics of the present invention is an aircraft aerodynamic analysis method for providing a graphical user interface (GUI) to perform an aerodynamic analysis of an aircraft using an open source (Open FOAM)

As shown in FIG. 8, may include a preprocessing step S100, an aerodynamic analysis step S200, and a post-processing step S300.

To learn more about each step,

The preprocessing step S100 may perform spatial division in a grid shape or a mesh shape so as to have a small volume on the surface and space of the aircraft using the open source provided by the preprocessing unit 100 have.

The preprocessing step (S100) inputs the size of the calculation area, the height and number of the lattice-size boundary layer around the aircraft as input variables of the open source, and generates a hexagonal lattice around the aircraft, To a polyhedral grid, and to generate a boundary-side grid to perform spatial division.

The aerodynamic analysis step S200 can analyze the aerodynamic force generated on the outside of the aircraft by using computational fluid dynamics (CFD) based on the open source provided by the aerodynamic analysis unit 200.

The aerodynamic analysis step (S200) inputs the type of the boundary surface, the range of the Mach number, the range of the angle of attack, the pressure and the temperature value of the remote boundary as input variables of the open source, The aerodynamic force generated on the outside of the aircraft can be analyzed.

The post-processing step (S300) receives the aerodynamic analysis data from the aerodynamic analysis step (S200) using the open source provided by the post-processing unit (300) have.

The post-processing step (S300) inputs the aerodynamic analysis data received from the aerodynamic analysis step (S200) as input variables of the open source to be provided. The force and moment at the aircraft and each interface and the lift coefficient Coefficients and moment coefficients can be extracted and output.

In other words, an aircraft aerodynamic analysis system and method using an open-source based computational fluid dynamics according to an embodiment of the present invention is optimized for aerodynamic analysis based on an open source in a preprocessing, post-processing and aerodynamic analysis processes Simple and light user GUI is built, 3 ~ 5 times analysis time compared to external time integration method. Shortening the time required and managing a series of preprocessing work from aircraft surface shape to grid generation by semi-automatic concept, The work can be simplified and the efficiency of work and the possibility of errors can be reduced.

Although the airborne aerodynamic analysis system and method using an open source based computational fluid dynamics according to an embodiment of the present invention have been described above, the airborne aerodynamic analysis system and method using the open source based computational fluid dynamics described above Those skilled in the art will readily understand that the program of the instructions for carrying out the present invention may be embodied in a recording medium that can be read by a computer or provided as a computer program written in computer instructions. In other words, it may be implemented in the form of a program command that can be executed through various computer means, recorded in a computer-readable recording medium, or may be a computer program written in an instruction word. The computer readable recording medium or the computer program may include program instructions, data files, data structures, and the like, alone or in combination. The program instructions recorded on the computer readable recording medium or the computer program may be those specially designed and constructed for the present invention or may be those known and available to those skilled in the computer software. Examples of the computer-readable recording medium or the computer program include magnetic media such as a hard disk, a floppy disk and a magnetic tape, optical media such as CD-ROM and DVD, optical disks such as floptical magneto-optical media such as disk, and hardware devices specifically configured to store and perform program instructions such as ROM, RAM, flash memory, USB memory, and the like. The computer-readable recording medium or the computer program may be a transmission medium such as a light or metal line, a wave guide, or the like, including a carrier wave for transmitting a signal designating a program command, a data structure, and the like. Examples of program instructions include machine language code such as those produced by a compiler, as well as high-level language code that can be executed by a computer using an interpreter or the like. The hardware device may be configured to operate as one or more software modules to perform the operations of the present invention, and vice versa.

As described above, the present invention has been described with reference to specific embodiments such as specific components and exemplary embodiments. However, the present invention is not limited to the above-described embodiments, And various modifications and changes may be made thereto by those skilled in the art to which the present invention pertains.

Accordingly, the spirit of the present invention should not be construed as being limited to the embodiments described, and all of the equivalents or equivalents of the claims, as well as the following claims, fall within the scope of the present invention .

100: preprocessing section
200: aerodynamic analysis unit
300: Post-
S100 to S300: Each step of the aircraft aerodynamic analysis method using the open-source computational fluid dynamics of the present invention

Claims (10)

An aircraft aerodynamic analysis system using computational fluid dynamics providing a graphical user interface (GUI) for performing an aerodynamic analysis of an aircraft using an open source (Open Foam)
Using the open source provided, a hexahedral grid is created around the aircraft so that it has a small volume on the surface of the aircraft and the space outside the aircraft, converts the hexahedral grid into a polyhedral grid by matching it with the shape of the aircraft, A preprocessing unit (100) for performing division;
Using the open source provided, CFD (Computational Fluid Dynamics) is used to simulate the 3D surface of the aircraft and the outer space of the aircraft through the wall boundary conditions of the LU-SGS numerical model and the turbulence model, An aerodynamic analysis (solver) unit 200 for analyzing the aerodynamic force generated in the vehicle; And
The aerodynamic analysis data received from the aerodynamic analysis unit 200 is processed using the provided open source to calculate the force and moment at the aircraft and each interface and the lift coefficient CL and the drag coefficient CD, Drag Coefficient), and a moment coefficient (CM, Moment Coefficient);
And an aircraft aerodynamic analysis system using computational fluid dynamics.
The method according to claim 1,
The preprocessing unit 100
And the height of the boundary layer, and the number of the boundary layer are input as input variables, and the aircraft aerodynamic analysis system using computational fluid dynamics.

The method according to claim 1,
The aerodynamic analysis unit 200
(AOA, Angle of Attack), the pressure and temperature of the remote boundary, and inputting them as input variables. Aircraft aerodynamic analysis system using computational fluid dynamics.
The method according to claim 1,
The post-processing unit 300
And an aerodynamic analysis data transmitted from the aerodynamic analysis unit (200) is input as an input variable.
A method of analyzing an aerodynamic aerodynamic force using computational fluid dynamics, which provides a graphical user interface (GUI) for performing an aerodynamic analysis of an aircraft using an open source (Open Foam)
Using the open source provided, a hexahedral grid is created around the aircraft so that it has a small volume on the surface of the aircraft and the space outside the aircraft, converts the hexahedral grid into a polyhedral grid by matching it with the shape of the aircraft, A preprocessing step (SlOO) for performing splitting;
Using the open source provided, CFD (Computational Fluid Dynamics) is used to simulate the 3D surface of the aircraft and the outer space of the aircraft through the wall boundary conditions of the LU-SGS numerical model and the turbulence model, An aerodynamic analysis step S200 for analyzing the aerodynamic force generated in the vehicle; And
(CL), a drag coefficient (CD), and a drag coefficient (CD), which are received from the aerodynamic analysis data of the aerodynamic analysis step (S200) using the provided open source, A post-processing step (S300) of extracting a moment coefficient (CM) and a drag coefficient, processing the extracted data as graph or graphical data, and providing the result;
Wherein the aircraft aerodynamic force analysis method is based on computational fluid dynamics.

6. The method of claim 5,
The preprocessing step (SlOO)
Wherein the size of the calculation area, the size of the grid around the aircraft, the height and number of the boundary layer are input and input as input variables.
6. The method of claim 5,
The aerodynamic analysis step (S200)
(AOA, Angle of Attack), the pressure and temperature of the far boundary, and inputting them as input variables. The method for analyzing aerodynamic forces of aircraft by computational fluid dynamics.
6. The method of claim 5,
The post-processing step (S300)
Wherein the aerodynamic analysis data received from the aerodynamic analysis step (S200) is input as an input variable.
A computer-readable recording medium storing a program for implementing an aircraft aerodynamic analysis method using computational fluid dynamics as set forth in any one of claims 5 to 8.
9. A computer program stored on a recording medium, the computer-readable recording medium having computer-executable instructions for implementing an aerodynamic analysis method using computational fluid dynamics according to any one of claims 5 to 8.

Images