Solution of unsteady rotational flow over supercritical wings

Ruo, S. Y.; Sankar, Lakshmi N.

doi:10.2514/6.1987-108

Cited by 5 publications

(4 citation statements)

References 3 publications

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“…(12)(13)(14)(15)(16)(17)(18)(19). The details of the scheme have been covered earlier by the authors in Refs.…”

Section: Methods Of Solutionmentioning

confidence: 99%

“…Hence, any computational scheme and the corresponding computer program can be easily converted to solve the set of Eqs. (12)(13)(14)(15)(16)(17)(18)(19).…”

Section: Methods Of Solutionmentioning

confidence: 99%

“…(14)(15)(16)(17)(18)(19), the resulting equations will not represent a conical flow. On the other hand, if the conical coordinates are used to transform the absolute motion equations, Eqs.…”

Section: Exact and Locally Conical Flowsmentioning

confidence: 98%

“…16 ' 18 Neither the TSD equation nor the FP equation can treat flows with strong shock waves or vortex-dominated flows. Very recently, time-accurate solutions of the Euler 19 ' 21 and Navier-Stokes equations 22 ' 23 have been presented with applications to two-dimensional unsteady transonic airfoil flows. A recent comprehensive review of the state-of-the-art of the computational unsteady transonic flows has been given by Edwards and Thomas 23 from the perspective of aeroelastic applications.…”

Section: Introductionmentioning

confidence: 99%

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Computation of steady and unsteady vortex-dominated flows with shockwaves

Kandil

Chuang

1988

AIAA Journal

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The unsteady Euler equations have been derived in the conservation form for the flow relative motion with respect to a rotating frame of reference. The resulting equations are solved by using a central-difference finitevolume scheme with four-stage Runge-Kutta time stepping. For steady flow applications local time stepping is used, and for unsteady applications the minimum global time stepping is used. A three-dimensional fully vectorized computer program has been developed and applied to steady and unsteady maneuvering delta wings. The capability of the three-dimensional program has been demonstrated for a rigid sharp-edged delta wing undergoing uniform rolling in a conical flow and rolling oscillations in a locally conical flow.

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“…(12)(13)(14)(15)(16)(17)(18)(19). The details of the scheme have been covered earlier by the authors in Refs.…”

Section: Methods Of Solutionmentioning

confidence: 99%

“…Hence, any computational scheme and the corresponding computer program can be easily converted to solve the set of Eqs. (12)(13)(14)(15)(16)(17)(18)(19).…”

Section: Methods Of Solutionmentioning

confidence: 99%