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

Heating Rate AAE 450 Spring 2008 Aerothermodynamics and Thermal Loads

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

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

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 http://www.grc.nasa.gov/WWW/K-12/airplane/atmosmet.html AAE 450 Spring 2008 Aerothermodynamics and Thermal Loads