1. 1 Jason Darby 2-14-08 Aerothermodynamics/Model Analysis Stagnation Point Heating Analysis

2. 2 Heating Rate Aerothermodynamics and Thermal Loads Lumped Heating at Solid Nosetip Method 0 1 2 Matlab code: *help from Vince Teixeira AAE450_Stag_heat_analysis.m Input: r_n, c_p, rho_w, emiss 3

3. 3 Heating Rate  Assumptions –Constant specific heats –No heat transfer within the body –Treat whole nosetip as one solid heat sink –Laminar flow at point 2 –No convective heating at point 3, only radiative –Wall temperature is the same at all 4 points Aerothermodynamics and Thermal Loads Future Work  Finish code for the heating analysis  Rule out testing for ablatives

4. 4 AAE 450 Spring 2008 Equations Aerothermodynamics and Thermal Loads M = 3, N = 0.5 for fully catalytic surface M 2 = 3.2 for laminar, flat plate = nose body radius = volume of solid nosetip

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