Consider a high speed vehicle flying at a standard altitude of 35 km, where the ambient pressure and temperature are 583 59 N m 2 and 246 1 K, respectively The radius of the spherical nose of the vehicle is 2 54 cm Assume the Prandtl number for air at these conditions is 0 72, that c p is 1008 joul...

a 1500 ms The answer is 416 5 W m 2 The aerodynamic heat transfer to the stagnation point can be calculated using the following equation Q qw qs where qw is the heat transfer from the wall to the flui ...

Consider a high-speed vehicle flying at a standard altitude of 35 km, where the ambient pressure and

Question:

Consider a high-speed vehicle flying at a standard altitude of 35 km, where the ambient pressure and temperature are 583.59 N/m² and 246.1 K, respectively. The radius of the spherical nose of the vehicle is 2.54 cm. Assume the Prandtl number for air at these conditions is 0.72, that c_p is 1008 joules/(kg K), and that the viscosity coefficient is given by Sutherland’s law. The wall temperature at the nose is 400K. Assume the recovery factor at the nose is 1.0. Calculate the aerodynamic heat transfer to the stagnation point for flight velocities of

(a) 1500 m/s,

(b) 4500 m/s.

From these results, make a comment about how the heat transfer varies with flight velocity.

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