STAGNATION POINT BOUNDARY LAYER WITH LARGE WALL-TO-FREESTREAM ENTHALPY RATIO,
Abstract
The effect of large surface-to-freestream enthalpy ratios on stagnation point shear and heat transfer is investigated for two-dimensional and axisymmetric bodies. Numerical solutions are obtained for a wide range of enthalpy ratios and wall transpiration rates. Absorption of externally imposed thermal radiation by the transpired gas is included for cases where the absorption is small compared to thermal conduction. It is found that the pressure gradient causes large velocity overshoot in the boundary layer. In the limit of infinite enthalpy ratio. the peak velocity in the boundary layer is approximately 4/9 or 1/3 that value that would occur at the wall for an inviscid two-dimensional or axisymmetric flow, respectively, with the same temperature ratio. The application of the numerical results to 'cold flow plus radiation' nose-tip test facilities is also noted. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1967
- Accession Number
- AD0661581
Entities
People
- Harold Mirels
- William E. Welsh Jr.
Organizations
- The Aerospace Corporation