Preliminary investigation at Mach number 1.9 of simulated wing-root inlets
Description:
Report presenting an experimental investigation to study several wing-root inlet configurations at Mach number 1.9. The inlets were of triangular and rectangular shape and external compression was provided by two-dimensional wedge surfaces. Results regarding the pressure-recovery and mass-flow data, effect of inlet side plates and curved diffusers, exit and inlet total-pressure distributions, improvement of exit total-pressure profiles, and inlet tests at zero flight speed are provided.
Date:
January 19, 1955
Creator:
Piercy, Thomas G. & Weinstein, Maynard I.
Item Type:
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Partner:
UNT Libraries Government Documents Department