THE APPLICATION OF A NONSIMILAR LAMINAR BOUNDARY LAYER ANALYSIS TO HYPERSONIC INLET COMPRESSION SURFACES,
Abstract
The report presents the results of an investigation in which the Smith and Clutter nonsimilar laminar boundary layer analysis is compared to experimental data and a modified linearized similar solution on typical hypersonic two-dimensional and axisymmetric inlet compression surfaces. The representative cases presented have a Mach number range of 11.6 to 16.87 and a unit Reynolds number of 60,000 to 400,000. For these conditions on the models investigated, the nonsimilar solution was found to treat transverse curvature as a first rather than a second order effect. Such factors as the input nondimensional boundary layer thickness, the distance between stations along the surface, and the selection of reference conditions were found to have an effect on the accuracy of the solution. The method showed satisfactory agreement with experimental data and the modified similar solution. Although not prohibitively long, the length of computer time suggests that the program should be used as a final design analysis tool rather than being applied in preliminary design stages. The detailed output of various quantities in the viscous layer makes the program particularly useful where temperature and velocity profiles are required. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1966
- Accession Number
- AD0654672
Entities
People
- Dennis Sedlock
Organizations
- Flight Dynamics Laboratory