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 language | English (US) |
|---|---|
| Title of host publication | AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting |
| Publisher | American Institute of Aeronautics and Astronautics Inc. |
| ISBN (Electronic) | 9781624104473 |
| DOIs | |
| State | Published - 2017 |
| Event | 55th AIAA Aerospace Sciences Meeting - Grapevine, United States Duration: Jan 9 2017 → Jan 13 2017 |
Other
| Other | 55th AIAA Aerospace Sciences Meeting |
|---|---|
| Country | United States |
| City | Grapevine |
| Period | 1/9/17 → 1/13/17 |
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ASJC Scopus subject areas
- Aerospace Engineering
Cite this
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 proceeding › Conference contribution
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TY - GEN
T1 - Three-dimensional flow features of swept impinging oblique shock/boundary-layer interactions
AU - Threadgill, James A S
AU - Stab, Ilona
AU - Doehrmann, Adam
AU - Little, Jesse C
PY - 2017
Y1 - 2017
N2 - 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.
AB - 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.
UR - http://www.scopus.com/inward/record.url?scp=85017223796&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85017223796&partnerID=8YFLogxK
U2 - 10.2514/6.2017-0759
DO - 10.2514/6.2017-0759
M3 - Conference contribution
AN - SCOPUS:85017223796
BT - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
ER -