cranfield0029

simpl model studi transient temperatur thermal stress distribut due aerodynam heat present work concern determin transient temperatur thermal stress simpl model intend simul part whole aircraft structur builtup varieti subject aerodynam heat first case consid convect heat transfer one side flat plate repres thick skin effect result temperatur distribut induc thermal stress associ bend restraint plate edg numer result present transient temperatur differenti plate environ temperatur first increas linearli time remain constant period linear increas repres time acceler aircraft correspond thermal stress inform present second case wide flang beam convect heat transfer outer face flang numer result present transient temperatur differenti wide rang valu applic paramet environ temperatur variat describ correspond thermal stress beam infinit length determin theoret analysi stress distribut beam finit length carri numer result obtain one case experiment investig temperatur stress beam describ result present indic good agreement correspond theoret result