Flight-testing of a channeled center-body axisymmetric supersonic inlet design concept was conducted at the National Aeronautics and Space Administration (NASA) Dryden Flight Research Center in collaboration with the NASA Glenn Research Center (Cleveland, Ohio) and TechLand Research, Inc. (North Olmsted, Ohio). This testing utilized the Propulsion Flight Test Fixture, flown on the NASA F-15B research test bed airplane (NASA tail number 836) at local experiment Mach numbers up to 1.50. The translating channeled center-body inlet was designed by TechLand Research, Inc. (U.S. Patent No. 6,276,632 B1) to allow for a novel method of off-design flow matching, with original test planning conducted under a NASA Small Business Innovative Research study. Data were collected in flight at various off-design Mach numbers for fixed-geometry representations of both the channeled center-body design and an equivalent area smooth center-body design for direct comparison of total pressure recovery and limited distortion measurements.
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机译：航空公司轴对称超音速入口设计概念的飞行测试在美国国家航空航天局（NASA）Dryden飞行研究中心与NASA Glenn Research Center（Cleveland，Ohio）和Techland Research，Inc。合作进行俄亥俄州北奥姆斯特德）。该测试利用了推进飞行试验夹具，在NASA F-15B研究试验台飞机（NASA尾部836）上，在当地实验马赫号高达1.50。通过Techland Research，Inc。（美国专利No.6,276,632 B1）设计了翻译的通道中心入口，以允许采用NASA小型企业创新研究研究中的原始测试规划的新设计流动匹配方法。数据在飞行中收集到各种非设计马赫号的航班，用于通道的中心设计和等效区域光滑的中心设计，用于直接比较总压力恢复和有限的失真测量。
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