Transonic off-design drag and performance of an axisymmetric inlet with 40 percent internal contraction on design /
by Richard R. Woollett, Edward T. Meleason, and David A. Choby.
Description
- Language(s)
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English
- Published
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Washington, D.C. : National Aeronautics and Space Administration ; 1974
- Summary
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An experimental investigation determined the drag and pressure performance of an axisymmetric supersonic inlet when operated in the transonic speed range. The inlet configuration was derived from a Mach 2.5 mixed compression inlet design with assumed variable geometry. At typical engine airflows the drag coefficient varied from 0.057 to 0.192 when the Mach number changed from 0.80 to 1.27. The presence of a wing simulator resulted in a sizable increase in total drag at Mach 1.2. This interference drag, which is roughly a 0.1 increase in drag coefficient, originates equally from an increase in both additive and cowl pressure drag.
- Note
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"NASA TM X-3042."
Performing organization report no.: E-7692.
"August 1974."
Cover title.
Also available online from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 9/19/16: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19740023304_1974023304.pdf.
- Physical Description
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53 p. :
ill. ;
27 cm.
Viewability
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University of Illinois at Urbana-Champaign
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