University of North Texas Digital Library (University of North Texas) · 1947 · 46 citations · 0 references
Open access
EngineeringAerospace EngineeringAerodynamicsAerospace StructuresComputational Fluid DynamicsAirfoil TheorySupersonic AerodynamicsWing AerodynamicsWing TheoryAerodynamic DragAspect Ratio EffectsDragMach NumberSupersonic Wing AerodynamicsThin Plate TheoryWave DragWing Aspect Ratio
From Summary: "The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at supersonic speeds was extended to include the effect of the region between the wing boundary and the foremost Mach wave from the wing leading edge. The effect of this region on the surface velocity potential has been determined by an equivalent function, which is evaluated over a portion of the wing surface. In this manner, the effect of angles of attack and yaw as well as the asymmetry of top and bottom wing surfaces may be calculated."