Effect of Leading-edge Load Constraints on the Design and Performance of Supersonic Wings1985 - 79 pages |
Common terms and phrases
02 O Flat ALPHA CN angle of attack best performance CAC CDC R/FT camber surfaces cambered wings CD L/D CM CDC R/FT DYN CL CD L/D CM CAC CDC CN CA CL coeffi Design and Analysis design Mach number drag due drag levels due to lift effect of leading-edge Figure 13 Figure B5 flat wing flow pattern flow separation FORCE DATA four wings GEOM 7 GEOM GEOM8 GEOM8 GEOM8 higher lift coefficients higher lift conditions L/D CM CAC leading edge leading-edge constraints leading-edge load constraints leading-edge vortices level of drag MACH 2.16 ALPHA Moderately constrained MN moderately constrained wing NASA number of 2.4 Oil flow pitching moment planform predicted PROJECT 1298 RUN R/FT DYN PRS root chord SDAS Severely constrained AC severely constrained wing shown in figure SPANWISE FLOW supersonic wing design Theoretical trailing edge uncon Unconstrained Moderately constrained UPWT PROJECT 1298 values of CL vortex flow wing model