Question: Consider an aircraft flying at Mach 3 at an altitude of 17,500m. Suppose the aircraft has a hemispherical nose with a radius of 30 cm. If it is desired to maintain the nose at 80°C, what heat flux must be removed at the stagnation point by internal cooling? As a fair approximation, assume that the air passes through a normal detached shock wave and then decelerates is entropically to zero at the stagnation point; then the flow near the stagnation point is approximated by low-velocity flow about a sphere.