NDLI: Preliminary investigation of a new type of supersonic inlet (Document No: 19930083137)

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Preliminary investigation of a new type of supersonic inlet (Document No: 19930083137)

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1951
Description	A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is considered. A particular arrangement with fixed geometry having a central body with a circular annular intake is analyzed, and it is shown theoretically that this arrangement gives high pressure recovery for a large range of Mach number and mass flow and therefore is practical for use on supersonic airplanes and missiles. For some Mach numbers the drag coefficient for this type of inlet is larger than the drag coefficient for the type of inlet with supersonic compression entirely inside, but the pressure recovery is larger for all flight conditions. The differences in drag can be eliminated for the design Mach number. Experimental results confirm the results of the theoretical analysis and show that pressure recoveries of 95 percent for Mach numbers of 1.33 and 1.52, 92 percent for a Mach number of 1.72, and 86 percent for a Mach number of 2.10 are possible, with the configurations considered. If the mass flow decreases, the total drag coefficient increases gradually and the pressure recovery does not change appreciably. The results of this work were first presented in a classified document issued in 1946.
File Size	1704350
Page Count	42
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930083137
Archival Resource Key	ark:/13960/t9s229t1t
Language	English
Publisher Date	1951-04-01
Access Restriction	Open
Subject Keyword	Diffusers, Supersonic Air Inlets - Nose, Annular Bodies, Ducted Nose Shape Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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