Computational Analysis of a Low-Boom Supersonic Inlet
- Chima, Rodrick V.
- November 2011.
- Physical Description:
- 1 electronic document
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available. and Free-to-read Unrestricted online access
- A low-boom supersonic inlet was designed for use on a conceptual small supersonic aircraft that would cruise with an over-wing Mach number of 1.7. The inlet was designed to minimize external overpressures, and used a novel bypass duct to divert the highest shock losses around the engine. The Wind-US CFD code was used to predict the effects of capture ratio, struts, bypass design, and angles of attack on inlet performance. The inlet was tested in the 8-ft by 6-ft Supersonic Wind Tunnel at NASA Glenn Research Center. Test results showed that the inlet had excellent performance, with capture ratios near one, a peak core total pressure recovery of 96 percent, and a stable operating range much larger than that of an engine. Predictions generally compared very well with the experimental data, and were used to help interpret some of the experimental results.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 20110023757., AIAA Paper 2011-3801., E-17906., NASA/TM-2011-217223., and 29th Applied Aerodynamics Conference; 27-30 Jun. 2011; Honolulu, HI; United States.
- No Copyright.
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