2.25: Advanced Fluid Dynamics Section 1: Continuum viewpoint and the equation of motion Section 2: Static Fluids Section 3: Mass Conservation Section 4: Inviscid flow - differential approach Section 5: Control Volume Theorums Section 6: Navier-Stokes equation and viscous flow Section 7: Similarity and dimensional analysis Section 8: Boundary layers, separation and effect on drag/lift Section 9: Vorticity and circulation Section 10: Potential flows; lift, drag and thrust production Section 11: Surface tension and its effect on flows Section 12: Introduction to turbulence Back to 2.25 Home | Back to Section 5
Problem 5.17: Rocket accellerating against gravity
 After its second booster has been fired, a space vehicle finds itself outside the earth's atmosphere moving vertically upward against gravity at speed V0. Its total mass at that point is M0. At t = 0, the vehicle's third stage is turned on and the rocket burns propellant at a mass rate of kg/s. Show that if the gravitational acceleration remains essentially constant at the rocket during the firing, the rocket’s velocity V(t) after time t will be given by where M(t) is the mass of the system at time t. Note that the pressure of the gas at the rocket exit plane, pe, will not be zero as it is in the ambient space, since the rocket exhaust is supersonic and hence the pressure at the exit is not in balance with the ambient pressure. The answer given above neglects the effect of the exit plane pressure on thrust.