Valeriy N. Golubkin  , Anatoly A. Gubanov  , Yuri G. Shvalev  and Vadim A. Talyzin

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_16501075

The results of thermal testing of high-speed aircraft model with the streamline-traced dorsal intake and internal power engine duct in the super/hypersonic TsAGI T-116 wind tunnel are presented. Boundary layer state on the compression intake surface was found to depend on a flight regime and particular type of turbulence stimulators. In addition to mass flow rate hysteresis found earlier, the boundary layer state hysteresis was discovered to accompany forward and reversed angle-of-attack change for definite types of turbulence stimulators. This and other factors influenced the intake start, are discussed.

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In Categories: Boundary Layer Control, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2018, Hypersonic Aerodynamics
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