Navier-Stokes, Flight, and Wind Tunnel Flow Analysis for the F/A-18 Aircraft PDF Download
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Author: Farhad Ghaffari
Publisher:
ISBN:
Category : Hornet (Jet fighter plane)
Languages : en
Pages : 72
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Book Description
Author: Farhad Ghaffari
Publisher:
ISBN:
Category : Hornet (Jet fighter plane)
Languages : en
Pages : 72
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Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781730800542
Category : Science
Languages : en
Pages : 68
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Book Description
Computational analysis of flow over the F/A-18 aircraft is presented along with complementary data from both flight and wind tunnel experiments. The computational results are based on the three-dimensional thin-layer Navier-Stokes formulation and are obtained from an accurate surface representation of the fuselage, leading-edge extension (LEX), and the wing geometry. However, the constraints imposed by either the flow solver and/or the complexity associated with the flow-field grid generation required certain geometrical approximations to be implemented in the present numerical model. In particular, such constraints inspired the removal of the empennage and the blocking (fairing) of the inlet face. The results are computed for three different free-stream flow conditions and compared with flight test data of surface pressure coefficients, surface tuft flow, and off-surface vortical flow characteristics that included breakdown phenomena. Excellent surface pressure coefficient correlations, both in terms of magnitude and overall trend, are obtained on the forebody throughout the range of flow conditions. Reasonable pressure agreement was obtained over the LEX; the general correlation tends to improve at higher angles of attack. The surface tuft flow and the off-surface vortex flow structures compared qualitatively well with the flight test results. To evaluate the computational results, a wind tunnel investigation was conducted to determine the effects of existing configurational differences between the flight vehicle and the numerical model on aerodynamic characteristics. In most cases, the geometrical approximations made to the numerical model had very little effect on overall aerodynamic characteristics. Ghaffari, Farhad Langley Research Center...
Author: Gary E. Erickson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 172
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 548
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722668686
Category :
Languages : en
Pages : 68
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Book Description
Computational analysis of flow over the F/A-18 aircraft is presented along with complementary data from both flight and wind tunnel experiments. The computational results are based on the three-dimensional thin-layer Navier-Stokes formulation and are obtained from an accurate surface representation of the fuselage, leading-edge extension (LEX), and the wing geometry. However, the constraints imposed by either the flow solver and/or the complexity associated with the flow-field grid generation required certain geometrical approximations to be implemented in the present numerical model. In particular, such constraints inspired the removal of the empennage and the blocking (fairing) of the inlet face. The results are computed for three different free-stream flow conditions and compared with flight test data of surface pressure coefficients, surface tuft flow, and off-surface vortical flow characteristics that included breakdown phenomena. Excellent surface pressure coefficient correlations, both in terms of magnitude and overall trend, are obtained on the forebody throughout the range of flow conditions. Reasonable pressure agreement was obtained over the LEX; the general correlation tends to improve at higher angles of attack. The surface tuft flow and the off-surface vortex flow structures compared qualitatively well with the flight test results. To evaluate the computational results, a wind tunnel investigation was conducted to determine the effects of existing configurational differences between the flight vehicle and the numerical model on aerodynamic characteristics. In most cases, the geometrical approximations made to the numerical model had very little effect on overall aerodynamic characteristics. Ghaffari, Farhad Langley Research Center...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 496
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 854
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 856
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Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 170
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 456
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