A tube-launched rocket has stabilizing fins at its rear. During launch the fins experience hot gas at Tg = 1700 oC for a time t = 0.3 seconds. It is important that the fins survive launch without surface melting, T. Given the heat transfer coefficient is h, the heat flux per unit area is q=h(Tg-Ts). What is the objective for this design? High melting point Low thermal conductivity Launching efficiency Low melting point

A tube-launched rocket has stabilizing fins at its rear. During launch the fins experience hot gas at Tg = 1700 oC for a time t = 0.3 seconds. It is important that the fins survive launch without surface melting, T. Given the heat transfer coefficient is h, the heat flux per unit area is q=h(Tg-Ts). What is the objective for this design? High melting point Low thermal conductivity Launching efficiency Low melting point

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter9: Heat Transfer With Phase Change

Section: Chapter Questions

Problem 9.4DP

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