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    A parametric experimental study of isolated rectangular nozzles (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A parametric study has been conducted in the Langley 16-Foot Transonic Tunnel on an isolated nonaxisymmetric fuselage, simulating a twin-engine fighter. The effects of aft-end closure distribution (top/bottom nozzle flap boattail angle vs. nozzle sidewall boattail angle) and afterbody/nozzle corner treatment (sharp or radius) were investigated. Four different closure distributions with three different corner radii were tested. Tests were conducted over a range of Mach numbers from 0.40-1.25 at zero degrees angle of attack. Solid plume simulators were used to simulate the jet exhaust.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 91-2136
    Format: text
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