Investigation of Boundry-Layer Transition on 10 deg Cone in Langley 4- by 4-Foot Supersonic Pressure Tunnel at Mach Numbers of 1.41, 1.61, and 2.01
Abstract
An investigation has been made to determine the transition Reynolds numbers on a 10 deg cone in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 and over a Reynolds number range from about 0.8 x 10(exp 6) to 9.5 x 10(exp 6) per foot. The results indicate that, on the average, the transition Reynolds numbers for a smooth cone increased with tunnel stagnation pressure from about 7 x 10(exp 6) at a test 4 x 10(exp 6) Reynolds number of per foot to approximately 8 x 10(exp 6) at a test Reynolds number of 9 x 10(exp 6) per foot for all test Mach numbers. There was no effect of Mach number on transition Reynolds number. The results also indicated that the transition point was unsteady and tended to oscillate approximately +/- 10 percent about the mean value of transition Reynolds number. A single-element two-dimensional surface roughness of one layer of 1/2-inch-wide and 0.005-inch-thick cellulose tape caused a larger decrease in transition Reynolds number than was experienced in low-speed or in other supersonic wind-tunnel investigations. The parameter of comparison was the ratio of transition Reynolds number for the rough cone to that for the smooth cone (Rt,r/Rt,av) for the same value of roughness height to boundary-layer displacement thickness at the roughness station (k/delta(*)k).
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1956
- Accession Number
- ADA377311
Entities
People
- Archibald R. Sinclair
- K. R. Czarnecki
Organizations
- National Aeronautics and Space Administration