MAE 113 Fundamentals of Propulsion Winter, 2011 Problem 1
Homework Assignment 5 Due: Thursday, February 17th in Class
Air enters a constant-area duct at M1 = 3, P1 = 1 atm, and T1 = 300 K. Inside the duct, the heat added per unit mass is q = 3 x 105 J/kg.
MAE 113 Fundamentals of Propulsion Winter, 2011 Problem 1 Water flows through a horizontal (x, y plane), 180 pipe bend as illustrated in figure 1. The flow cross-sectional area is constant at a value of 0.2 ft2 everywhere along the pipe. The magnitude of
MAE 113, Home Work 4, Due February 11, 2016
1. Standard atmospheric air at stagnation temperature, T0 = 288 K and
stagnation of p0 = 1 bar flows from a friction-less adiabatic converging
nozzle into a friction-less diabatic constant area duct. Heat is add
MAE 113, Home Work 5, Due February 25, 2016
1. The velocity profile in the boundary layer over a flat plate is presumed
to be given by u/U = (3/2) (1/2) 3 , where = y/ with y the
coordinate normal to the plate and the boundary layer thickness.
2 )](Re )0.
MAE 113 Fundamentals of Propulsion Winter, 2011 Problem 1
Homework Assignment 4 Due: Thursday, February 10th in Class
Consider the flow through a rocket engine converging-diverging nozzle shown in figure 1. Assume that the gas flow through the nozzle is a
MAE 113 Fundamentals of Propulsion Winter, 2011
Homework Assignment 3 Due: Thursday, January 27th in Class
Problem 1 An ideal gas flows adiabatically through a duct. At section (1), p1 = 140 kPa, T1 = 260C, and V1 = 75 m/s. Farther downstream, P2 = 30 kPa