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Pressure-Distribution Measurements on a Full-Scale Horizontal Tail Surface for a Mach Number Range of 0.20 to 0.70

Carl F Schueller

Abstract

Report presenting testing of a full-scale, semispan, horizontal tail surface for a jet-propelled fighter airplane in the 16-foot high-speed tunnel to determine the variation of the chordwise and spanwise pressure distributions with Mach number. Surface irregularities were found to cause appreciable distortion of the pressure distribution. Results regarding chordwise distributions, spanwise distribution, effect of Mach number on root bending moment, and estimated critical Mach numbers are provided.

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Available abstract

Key concepts: Mach number, Jet (fluid), Mechanics, Range (aeronautics), Mach wave, Distortion (music), Airplane, Surface (topology)