Correction: Aerodynamic Heating Coupled with Structural Temperature Response Analysis for Hypersonic Flight Vehicles

Correction Notice1. Figures 3 and5 were derived from similar figures in Reference 1 (J.D. Anderson) 2. Figure A.1, in Appendix A, was derived from a similar figure in Reference 9 (F.M. White) 3. Figure 13: Replicating the "Model" results requires additional input: in this case, the Space Shuttle Mission STS-3 post-flight Best Estimate Trajectory (STS-3 BET).The STS-3 BET was obtained from the National Aeronautics and Space Administration (NASA).4. On page 9, first paragraph after Equation ( 23), the fourth sentence states: "The higher temperatures where air begins to diverge from ideal gas properties are typically experienced by a flying vehicle when freestream M > 10." Instead, the above statement should read as follows: "As freestream Mach numbers approach 5 and above, flight vehicles begin to experience temperatures, which cause local flow conditions to gradually diverge from their ideal gas properties.These differences become much more significant as freestream Mach numbers approach 10 and above."