Org Retractable
calculate the atmospheric drag on a rocket?
A small rocket is launched from a cannon in Ecuador of the Earth at sea level, P = 1 atm. T = 25 ° C. The rocket consists of a cylinder, length = 1.2 m in diameter = 0.4 m, and a parabolic cone, retractable fins, motor, fuel, and payload, total mass = 450 kg. In the canon muzzle, if the speed is 6.0 km / s, 1. calculate the force of air friction, in http://en.wikipedia.org/wiki/Drag_ Newton (physics) Drag_at_high_velocity # 2. calculate the heat in W / m² in the nose 3. what these values if the nose is dimpled the surface like a golf ball?
Its small rocket drag does not have that great of a profile: Too Stuby. On the other hand, travels at supersonic speeds (Mach 18). I have no information on CD at supersonic speeds. Suppose a Cd =. 3 F = 1 / 2 ρ v ρ Cd ^ 2 A at 25C = 1.184 kg / m ^ 3 ^ A = π / 4 d ^ 2 Fd = 8.03×10 5 N b. Heating = F-speed drive * / A = H 3.8 x 10 ^ 10 W / m ^ 2 Note, I used the cross-sectional area, if you replace one hemisphere, would be 1 / 2 the value of which does not account for heating the air. Most of the heating is carried in the air. c. Dimples are to help in the transition from laminar to convective flow and to avoid flow separation. Given the hypersonic speed and large Reynolds number, I doubt would dimples nothing.
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