Three-dimensional flow features of swept impinging oblique shock/boundary-layer interactions

James A S Threadgill, Ilona Stab, Adam Doehrmann, Jesse C Little

Research output: Chapter in Book/Report/Conference proceedingConference contribution

6 Citations (Scopus)

Abstract

An experimental investigation has been conducted to assess the flow structure in the interaction of a swept impinging oblique shock with a turbulent boundary layer. While representing a fundamentally simplified non-dimensional interaction, the behavior of flow in this geometry has not been assessed at Mach numbers below the hypersonic regime. Three angles of sweep (ψsg = 0:0°, 22:5°, and 40:0°) have been assessed on a shock genera- tor with x-y plane deflection angle of θsg = 12:5° in Mach 2.3 and Mach 3.0 incoming flow with a turbulent boundary layer using a combination of pseudo-color schlieren photography and oil-flow visualization. Significant flow three-dimensionality is observed when testing without endplates to the point where a quasi-2D impinging oblique shock cannot be established. After limiting leakage at the shock generator root and increasing the aspect ratio of the interaction channel, quasi-infinite span interactions have been induced for all swept cases and visualized here. In addition, a 3D inviscid model of the interaction has been constructed to determine the onset of inviscid detachment - previously associated with the cylindrical-conical interaction development boundary. However, experimental results suggest that the onset of conical interactions is below that predicted by the inviscid model, in agreement with similar observations on swept compression ramps.

Original languageEnglish (US)
Title of host publicationAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624104473
DOIs
StatePublished - 2017
Event55th AIAA Aerospace Sciences Meeting - Grapevine, United States
Duration: Jan 9 2017Jan 13 2017

Other

Other55th AIAA Aerospace Sciences Meeting
CountryUnited States
CityGrapevine
Period1/9/171/13/17

Fingerprint

Mach number
Boundary layers
Hypersonic aerodynamics
Photography
Flow structure
Flow visualization
Aspect ratio
Color
Geometry
Testing
Oils

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Threadgill, J. A. S., Stab, I., Doehrmann, A., & Little, J. C. (2017). Three-dimensional flow features of swept impinging oblique shock/boundary-layer interactions. In AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting [AIAA 2017-0759] American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2017-0759

Three-dimensional flow features of swept impinging oblique shock/boundary-layer interactions. / Threadgill, James A S; Stab, Ilona; Doehrmann, Adam; Little, Jesse C.

AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2017. AIAA 2017-0759.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Threadgill, JAS, Stab, I, Doehrmann, A & Little, JC 2017, Three-dimensional flow features of swept impinging oblique shock/boundary-layer interactions. in AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting., AIAA 2017-0759, American Institute of Aeronautics and Astronautics Inc., 55th AIAA Aerospace Sciences Meeting, Grapevine, United States, 1/9/17. https://doi.org/10.2514/6.2017-0759
Threadgill JAS, Stab I, Doehrmann A, Little JC. Three-dimensional flow features of swept impinging oblique shock/boundary-layer interactions. In AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc. 2017. AIAA 2017-0759 https://doi.org/10.2514/6.2017-0759
Threadgill, James A S ; Stab, Ilona ; Doehrmann, Adam ; Little, Jesse C. / Three-dimensional flow features of swept impinging oblique shock/boundary-layer interactions. AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2017.
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