Three-dimensional swept shock/turbulent boundary-layer separations with control by air injection

Title

Three-dimensional swept shock/turbulent boundary-layer separations with control by air injection

 Author

Peake, D.J.

Institution

National Research Council Canada, National Aeronautical Establishment, High Speed Aerodynamics Laboratory

 Date

1976-07-31

 Abstract

Experimentally determined wall pressure distributions, local surface shear stresses and their directions, and detailed turbulent boundary-layer traverses in near zero heat transfer conditions, are presented through skewed shock/boundary-Iayer interaction regions generated by a wedge standing normal to a test wall. The mainstreamMach numbers were 2 and 4, while the Reynolds number based on the undisturbed test boundary-layer thickness of 0.2-in., growing along the nozzle sidewall of the NAE 5 X 5-in. blowdown wind tunnel, was -2 X 105. Tangential air injection at a jet exit Mach number of 3 was then introduced into the 3D shock separated Mach 2 boundary layer, to control the separation. The optimum direction of blowing was found to be along a line somewhere between the deflected surface of the wedge and the line of the oblique shock wave

 To reference this document use:

http://resolver.tudelft.nl/uuid:70753c08-a031-416c-886e-db80f6b34d95

 Publisher

National Research Council Canada

 Access restriction

Campus only

 Source

National Research Council Aeronautical Report LR 592

 Part of collection

Aerospace Engineering Reports

 Document type

report

 Rights

(c)1976 National Research Council Canada
Files
PDF LR-592.pdf 32.86 MB
Close viewer