A Collection of Technical Papers: AIAA 5th Applied Aerodynamics Conference, August 17-19, 1987, Monterey, California |
Contents
AIAA NUMBER PAGE NUMBER | 1 |
Euler and NavierStokes Solutions for the Leeside Flow Over Delta Wings | 14 |
Euler Analysis of the AFWAL 65 Delta Wing J R SIRBAUGH | 34 |
47 other sections not shown
Common terms and phrases
aerodynamic AIAA AIAA Paper aircraft analysis angle of attack aspect ratio aspect ratio wings body boundary layer calculated camber canard characteristics chine chord Comparison computed configuration contours deflection delta wing downstream drag coefficient effects equation Euler Euler equations experimental data flap flight flow field flow visualization forebody freestream fuselage geometry grid inboard increase induced inviscid iterations laminar leading edge leading-edge lift coefficient lower surface Mach number maximum lift method modifications NASA Navier-Stokes Navier-Stokes equations obtained panels pitching moment plane planform potential predicted presented pressure coefficient pressure distribution region Reynolds number root chord separation shock shown in figure solution span spanwise speed stability stall station strake supersonic surface pressure test section three-dimensional tion tip vortex trailing edge trailing-edge transonic turbulent unsteady upper surface values velocity vertical tail viscous vortex flow vortices wake wall waverider wind tunnel winglet