Fundamental Studies of SUBSONIC and Transonic Flow Separation. Part 3. Third Phase Summary Report
Abstract
The work reported herein represents the third phase of a fundamental study of transonic flow separation with extensive experimental measurements and some numerical Navier-Stokes solutions for high Reynolds number two-dimensional flow. The flow conditions have been extended to include low supersonic free- stream cases. The tests were performed over a Mach number range of 0.6 and 1.32 and Reynolds number range of 4 to 200 million. Simple geometrical surface and flow discontinuities of different sizes (such as ramps, rearward and forward- facing steps, cylinders, etc.) were selected to cause upstream disturbances and/ or generate downstream adverse pressure gradient regions strong enough to produce local flow separation. The incipient separation angle in flow over ramp compression corner was measured. An average incipient separation angle of 22.5 degrees was confirmed, with no Reynolds number effect in the above range of free-stream flow parameters.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1979
- Accession Number
- ADA074868
Entities
People
- A. Vakili-dastjerd
- F. G. Collins
- Jingen Wu
- K. C. Reddy
- T. H. Moulden
Organizations
- University of Tennessee Space Institute