BOUNDARY-LAYER TRANSITION ON A GROUP OF BLUNT NOSE SHAPES AT A MACH NUMBER OF 2.20
Abstract
The boundary-layer transition on six axisymmetrical blunt bodies of revolution was studied. Model shapes were selected with respect to the degree of favorable pressure gradient over the model surface. Tests were conducted at a Mach number of 2.20 and over a range of free-stream Reynolds number per foot of about 1.4 x 10 to the 6th power to 6.5. The tests were made at an angle of attack of 0 deg. with zero heat transfer. For the hemisphere, the flow remained essentially laminar over the model surface length for the entire pressure range of the tests. For a strong favorable pressure gradient followed by any weak favorable, neutral, or adverse gradient, the tendency was for transition to occur at or immediately behind the shoulder. A single strip of threedimensional roughness in the region of strong favorable pressure gradient did not fix transition on the models at the roughness location except at the maximum test pressures, whereas a second roughness strip added in a region of neutral or adverse pressure gradient did fix transition. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1961
- Accession Number
- AD0260641
Entities
People
- K.r. Czarnecki
- Mary W. Jackson
Organizations
- National Aeronautics and Space Administration