Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

<table class="table-group" id="tab3"><tr><td><table class="table"><tr><td class="thead-hr" colspan="3"><hr/></td></tr><tr class="thead"><td class="align_left">Panel regions</td><td class="align_center">Windward</td><td class="align_center">Leeward</td></tr><tr><td class="thead-hr" colspan="3"><hr/></td></tr><tr><td class="align_left">Nose region</td><td class="align_center">Modified Newtonian</td><td class="align_center">Prandtl-Meyer</td></tr><tr><td class="align_left">Wing-body region</td><td class="align_center">Tangent cone (corrected)</td><td class="align_center">Prandtl-Meyer</td></tr><tr class="table-tr"><td colspan="3"><hr class="tbody-hr"/></td></tr></table></td></tr></table>

<div>Selected impact methods for aerodynamic computations.</div>

International Journal of Aerospace Engineering

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Table 3

Table 3: Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects 