cranfield0025

inviscid hyperson flow blunt nose slender bodi hyperson speed drag area blunt nose much larger drag area slender afterbodi energi contain flow field plane right angl flight direct nearli constant downstream distanc mani time greater characterist nose dimens transvers flow field exhibit certain similar properti directli analog flow similar behind intens blast wave found taylor lin sakurai comparison experi hammitt bogdonoff flat plate blunt lead edg helium show shock wave shape predict accur similar analysi predict surfac pressur distribut somewhat less satisfactori experiment result hemispher cylind obtain galcit air tunnel indic shock wave shape also surfac pressur bodi given close similar theori except near hemispher cylind junction energi consider combin detail studi equat motion show flow similar also possibl class bodi form provid two dimension bodi bodi revolut shock shape similar bodi shape entir flow field distanc nose must depend extent detail nose geometri util energi drag consider one find hyperson speed inviscid surfac pressur gener blunt lead edg larger pressur induc boundari layer growth insul flat surfac insul blunt nose slender bodi revolut correspond distanc given free stream reynold number base lead edg thick nose diamet free flight constant replac respect viscou interact effect import forward portion bluntnos slender bodi rel low valu howev far downstream nose inviscid pressur small viscou interact phenomena taken account