The infinitesimal, second order character of local Mach number variations in calculations of nose cone heating, either from athermanous temperature or from the transfer coefficient found with the local Nusselt number
Abstract
The difference between the athermanous temperature calculated using nose cone upstream aerodynamic characteristics on the one hand, and on the other, using local aerodynamic characteristics is determined. The flow velocity is given by the St. Venant formula. The coefficient of compression on the nose cone is introduced. The calculation of the athermanous temperature is explained, and a numerical application leads to a very good second order approximation. The error is shown maximal at M = 6, given ambient temperature. It is thus unnecessary to know the local Mach numbers along a nose cone in order to calculate heating accurately.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- March 1980
- Bibcode:
- 1980STIN...8127451D
- Keywords:
-
- Aerodynamic Heating;
- Mach Number;
- Nose Cones;
- Approximation;
- Gas Flow;
- Heat Transfer Coefficients;
- Nusselt Number;
- Pressure Gradients;
- Saint Venant Principle;
- Shock Fronts;
- Fluid Mechanics and Heat Transfer