cranfield0049

temperatur veloc profil compress laminar boundari layer arbitrari distribut surfac temperatur analysi present enabl temperatur profil veiociti profil heat transfer skin friction calcul laminar flow two dimension axial symmetr surfac without pressur gradient arbitrari analyt distribut surfac temperatur gener theori applic prandtl number although numer result given herein comput air predict theori special case constant surfac temperatur compar calcul crocco basi comparison infer present theori enabl heat transfer skin friction calcul accur within per cent made flight condit mach number near within per cent superson wind tunnel condit consider higher mach number particular effort made present result simpl consid gener form use readili practic applic mathemat point view theori applic arbitrari analyt distribut surfac temperatur given practic case necessari surfac temperatur distribut approxim polynomi unknown final equat develop coeffici polynomi work involv appli theori given case depend entir work involv approxim given surfacetemperatur distribut polynomi exampl work detail illustr princip effect variabl surfac temperatur shown posit infinit neg infinit heat transfer coeffici occur anomali infinit neg heat transfer coeffici discuss attribut customari definit heat transfer coeffici shown fundament inappropri flow variabl surfac temperatur particular exampl consid convent method calcul net heat transfer yield complet incorrect result brief qualit discuss possibl effect heat transfer flow separ given order facilit use result princip equat develop collect summar section entitl practic use result