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Aerodynamic characteristics of two delta wings at Mach number 4.04 and correlations of lift and minimum-drag data for delta wings at Mach numbers from 1.62 to 6.9

Edward F Ulmann, Robert W. Dunning

Abstract

Report presenting tests of the aerodynamic characteristics of two delta wings of the same aspect ratio and airfoil sections at Mach number 4.04. The results indicated that the ratio of the experimental lift-curve slope to the theoretical two-dimensional lift-curve slope from previous testing is valid at this Mach number.

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Available abstract

Key concepts: Mach number, Aerodynamics, Vortex lift, Drag divergence Mach number, Lift (data mining), Airfoil, Lift-to-drag ratio, Delta wing