Hypersonic and Other Viscous Interactions
Abstract
Surface heat transfer and boundary layer transition measurements have been performed on a slender blunted cone at M(infinity) = 8.0. These measurements have been obtained on the conical surface with mass transfer occurring on the spherical nose cap. The free stream Reynolds number, based on nose radius, varied between 6000 and 90000. Data was obtained both at zero angle of attack and at angles as high as 14 deg, which exceeds the semi-vortex cone angle of 10 deg. The technique utilized in the determination of transition location was a thin film gauge, on the model surface, which was maintained at a constant temperature by an anemometer system. The RMS output of the film gauge was found to accurately locate the onset of boundary layer transition. A numerical analysis of film cooling in the stagnation region of a slender cone was also performed using the thin shock layer approximation. The porous region was analyzed and compared to previously obtained results using different assumptions. The downstream region, at angle of attack, utilize the porous region results as initial conditions. The computer program, however, was not successfully operated in this mode.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1982
- Accession Number
- ADA121237
Entities
People
- Martin H. Bloom
- Robert J. Cresci