Topic: Fluid Mechanics
A rocket exists exhaust gases with rho = 0.5 kg/m³ out a 50 cm diameter nozzle at a velocity of 1200 m/s. The thrust, is
- A. 420 kN
- B. 280 kN
- C. 140 kN
- D. 90 kN
Answer: C. 140 kN
Explanation: Area of Nozzle A = (pi/4) * (0.5)^2 = 0.196 m². Thrust = rho * A * V² = 0.5 * 0.196 * (1200)^2 = 141300 N = 141.3 kN, which is closest to 140 kN.