cranfield0082

theoret investig ablat glass type heat protect shield vari materi properti stagnat point enter irbm melt type heat protect stagnat point enter irbm treat employ homogen opaqu nondecompos glass shield exceed temperatur effect due variat glass properti ballist entri vehicl nose diamet ballist factor entri angl vertic altitud entri speed perform differ glass shield assum combin materi properti investig employ calcul method yield practic exact transient solut problem corollari result certain steadi flight state also given discuss made possibl deriv realist flight condit thermal characterist employ thin light weight glass shield investig hypothet glass shield lead conclus low thermal conduct high specif heat thu small thermal diffus desir small thermal diffus yield high surfac temperatur caus high radi heat transfer shield steep temperatur profil normal surfac caus small thermal penetr across shield littl total ablat shield result show assum irbm entri necessari thick employ glass shield increas monoton thermal diffus materi paramet affect thick high viscos level high emiss constant surfac supposedli opaqu shield also desir although two properti exert compar small influenc overal perform disregard glass shield extrem low viscos level