Computation of supersonic viscous flows around pointed bodies at large incidence

Degani, David; Schiff, Lewis B.

doi:10.2514/6.1983-34

Cited by 81 publications

(22 citation statements)

References 6 publications

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“…The thin-layer approximation negle c ts derivatives of the visc ous stresses in the flow direc tion . Baldwin and Lomax (1978) Schiff (1983) and Visbal and Knight (1983).…”

Section: Solution Methods and Turbulence Modelsmentioning

confidence: 99%

Modeling of Turbulent Separated Flows for Aerodynamic Applications

Marvin

1986

Recent Advances in Aerodynamics

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“…The thin-layer approximation negle c ts derivatives of the visc ous stresses in the flow direc tion . Baldwin and Lomax (1978) Schiff (1983) and Visbal and Knight (1983).…”

Section: Solution Methods and Turbulence Modelsmentioning

confidence: 99%

Modeling of Turbulent Separated Flows for Aerodynamic Applications

Marvin

1986

Recent Advances in Aerodynamics

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“…The modifications adopted here, similar to those proposed in Ref. 12, ensure that the outer eddy viscosity is correctly scaled relative to the leeside boundary layer rather than the vortex core.…”

Section: Theorymentioning

confidence: 97%

Vortical flow over an elliptical-body missile at high angles of attack

Newsome

Adams

1988

Journal of Spacecraft and Rockets

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Numerical solutions to the Reynolds-averaged Navier-Stokes equations are given for the flow about an elliptical body missile (3:1 ellipse) at a Mach number of 2.5 and a Reynolds number of 4.66 x 10 6 based on body length. At high angles of attack, the flow is dominated by large-scale free vortices that occur in the leeside flowfield due to crossflow boundary-layer separation. Emphasis is focused on the accurate prediction of the leeside vortical flow. Solutions are presented for both symmetric and asymmetric (body rolled 45 deg) configurations at 10 and 20 deg angles of attack. The computed results are compared with experimental surface pressure measurements and vaporscreen photographs. Excellent agreement is obtained in all cases.

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“…The model was further upgraded with the Degani-Schiff modi cation. 16 To accommodatethe large three-dimensionaleffects due to complexity of geometry, high angle of attack involved the B-L model has been extended to three-dimensional ows. 8 …”

Section: Flow Solver and Turbulence Modelmentioning

confidence: 99%

Effect of External Components on V-22 Aircraft Forward-Flight Aerodynamics

Tai

2000

Journal of Aircraft

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The effects of protuberances, forward-looking infrared, AAR47 sensor fairing, and refueling boom on V-22 forward ight aerodynamics using computational uid dynamics are investigated. The multizone Navier-Stokes method is applied to the ow over a complete V-22 wing-fuselage-nacelle con guration, with and without external components. The angle of attack varies from 0 to 16 deg in forward ight. A slight increase in drag is found at 0-deg angle of attack for an aircraft con gured with the external units; this effect decreases as the angle of attack increases from zero to moderate values. However, at high angles of attack, the added ow disturbances due to attachments seems to worsen tail buffeting and lift-to-drag ratio. The numerical results are in general agreement with recent ight test data.

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Computation of supersonic viscous flows around pointed bodies at large incidence

Cited by 81 publications

References 6 publications

Modeling of Turbulent Separated Flows for Aerodynamic Applications

Modeling of Turbulent Separated Flows for Aerodynamic Applications

Vortical flow over an elliptical-body missile at high angles of attack

Effect of External Components on V-22 Aircraft Forward-Flight Aerodynamics

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