1. Jason Darby 1-31-08 Aerothermodynamics Stagnation Point Heating Analysis
AAE 450 Spring 2008

2. Heating Rate
AAE 450 Spring 2008
Aerothermodynamics and Thermal Loads

3. Heating Rate Future Work Assumptions Incompressible Flow Ground Launch
Refine code for the heating analysis
Use SODDIT to test for ablative TPS
AAE 450 Spring 2008
Aerothermodynamics and Thermal Loads

4. Equations q_dot = C*rho^N*V^M C = (1.83e-8)*r_n^(-0.5)*(1-g_w)
g_w = h_w/h_o = wall enthalpy/total enthalpy
h_w = c_pw*T_w
h_o = h_a + 0.5*V^2
h_a = c_pa*T_a
AAE 450 Spring 2008
Aerothermodynamics and Thermal Loads

5. References
Anderson Jr., John D., “Hypersonic and High-Temperature Gas Dynamics”, 2nd ed., AIAA, Reston, VA, 2006.
Schneider, Steven P., “Methods for Analysis of Preliminary Spacecraft Designs”, AAE450, Spacecraft Design, Purdue University
AAE 450 Spring 2008
Aerothermodynamics and Thermal Loads