Transonic flowfields about transport and fighter aircraft are modeled using the thin-layer and slender-layer approximations to the unsteady compressible Reynolds-average Navier-Stokes equations. The equations are solved by an explicit multi-stage Runge-Kutta time-stepping method using a finite-volume formulation on body-conforming curvilinear grids. Convergence acceleration and vectorization enhance code efficiency. Microtasking allows effective use of all available processors on a Cray X/MP-48. Results are compared with experimental data for typical fighter and transport configurations.
Navier-Stokes calculations of transonic viscous flow about wing-body configurations
Navier-Stokes-Berechnung der viskosen Ueberschallstroemung um Rumpf und Tragflaechen
AIAA-Papers ; Jul ; 1-10
1987
10 Seiten, 8 Bilder, 15 Quellen
Conference paper
English
STROEMUNGSVORGANG , FLUGZEUGZELLE , TRAGFLUEGEL , AUSSENAERODYNAMIK , VISKOELASTISCHE STROEMUNG , TRANSPORTFLUGZEUG , MILITAERFLUGZEUG , UMSTROEMUNG , NAVIER-STOKES-GLEICHUNG , UEBERSCHALLSTROEMUNG , REYNOLDS-ZAHL , INSTATIONAERE STROEMUNG , LOESUNG (ERGEBNIS) , GITTERGEOMETRIE , NAEHERUNGSVERFAHREN , RECHNERSIMULATION
Navier-Stokes Simulation of a Transonic Wing-Body Configuration
British Library Conference Proceedings | 1993
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