Steady and unsteady full potential calculation for large and small aspect ratio supercritical wings

Ruo, S. Y.; Malone, John B.; Sankar, Lakshmi N.

doi:10.2514/6.1986-122

Cited by 3 publications

(5 citation statements)

References 2 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%

“…Figures 4b and 4c show the crossflow velocity and crossflow Mach contours at / = 2. 16 Figure 5a shows the surface pressure covering the range of time steps 4001-6000. The peak suction pressure on the left is moving to the left as the vortex is disappearing, and an attached flow is developing.…”

Section: Rolling Oscillation Of a Wing In A Locally Conical Flowmentioning

confidence: 99%

“…In the unsteady transonic flow area, most of the available computational schemes are based on the time-accurate solution of the transonic small disturbance (TSD) equation 14 ' 15 and the time-accurate solution of the full-potential (FP) equation. 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.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

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%