Title: Preliminary Investigation of a Submerged Inlet and a Nose Inlet in the Transonic Flight Range with Free-fall Models
Abstract: Memorandum presenting an NACA submerged inlet and an NACA series I nose inlet installed in bodies of 12.4 fineness ratio to determine the drag and pressure-recovery characteristics of each body-inlet configuration. The tests were conducted with large-scale free-fall models released at an altitude of 40,000 feet, for mass-flow ratios of about 0.4 and 0.7 over a Mach number range of about 0.70 to 1.10. Results regarding drag and ram-recovery ratios are provided.
Publication Year: 1951
Publication Date: 1951-06-18
Language: en
Type: article
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Cited By Count: 2
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