Flight determination of the drag of conical-shock nose inlets with various cowling shapes and axial positions of the center body at Mach numbers from 0.8 to 2.0
Description: Report presenting free-flight testing of conical-shock nose inlet models with cowls of fineness ratio 3 with five different profiles. Three of the profiles were mostly conic with different lip shapes, one was parabolic, and one was NACA 1-series. Results regarding the basic data, effect of cone position, comparison of profile shapes, and effect of mass-flow ratio are provided.
Date: September 10, 1954
Creator: Merlet, Charles F. & Putland, Leonard W.
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Partner: UNT Libraries Government Documents Department