The jet has a speed of 1260 km/hkm/h when it is flying horizontally. Air enters the intake scoop S� at the rate of 52 m3/sm3/s. The engine burns fuel at the rate of 1.85 kg/skg/s, and the gas (air and fuel) is exhausted relative to the plane with a speed of 2330 km/hkm/h. The plane has a mass of 8 MgMg. Assume that the air has a constant density of ρa�� = 1.112 kg/m3kg/m3. (Figure 1)   Determine the drag exerted on the plane by air resistance. Express your answer to three significant figures and include the appropriate units

The second stage of a two-stage rocket weighs 2000 lb (empty) and is launched from the first stage with a velocity of 3000 mi/h. The fuel in the second stage weighs 1000 lb. If it is consumed at the rate of 50lb/s and ejected with a relative velocity of 8000 ft/s, determine the acceleration of the second stage just after the engine is fired. What is the rocket’s acceleration just before all the fuel is consumed? Neglect the effect of gravitation.

A rocket lifts off from Earth initially at a mass of 50,000 kg. If it burns 40,000 kg of fuel during 40 seconds, it increases its speed by 5 km/s. 1. What is the exhaust velocity of the rocket? 2. What is the mass loss rate of the rocket? 3. What is the thrust of the rocket?

The missile weighs 47000 lb. The constant thrust provided by the turbojet engine isT = 18000 lb. Additional thrust is provided by two rocket boosters B. The propellant ineach booster is burned at a constant rate of 175 lb/s, with a relative exhaust velocity of 2000f t/s. If the mass of the propellant lost by the turbojet engine can be neglected, determinethe velocity of the missile after the 6 s burn time of the boosters. The initial velocity ofthe missile is 150 mi/h. Using your integration procedure from the previous labs solve thisproblem with n = 5, n = 10 and n = 100.