Questions from Fundamentals of Aerodynamics

Q: Repeat Problem 7.9, considering a point on the airfoil

Repeat Problem 7.9, considering a point on the airfoil surface where the pressure is 0.3 atm.

Q: Repeat Problem 7.10, considering the flow of Problem 7

Repeat Problem 7.10, considering the flow of Problem 7.11.

Q: Bernoulli’s equation, Equation (3.13), (3.

Bernoulli’s equation, Equation (3.13), (3.14), or (3.15), was derived in Chapter 3 from Newton’s second law; it is fundamentally a statement that force=mass*acceleration. However, the terms in Bernoul...

Q: Calculate cp, cv, e, and h for a

Calculate cp, cv, e, and h for a. The stagnation point conditions given in Problem 7.1 b. Air at standard sea level conditions (If you do not remember what standard sea level conditions are, find them...

Q: Just upstream of a shock wave, the air temperature and pressure

Just upstream of a shock wave, the air temperature and pressure are 288 K and 1 atm, respectively; just downstream of the wave, the air temperature and pressure are 690 K and 8.656 atm, respectively....

Q: Consider the isentropic flow over an airfoil. The freestream conditions are

Consider the isentropic flow over an airfoil. The freestream conditions are T∞ = 245 K and p∞ = 4.35 × 104 N/m2. At a point on the airfoil, the pressure is 3.6 × 104 N/m2. Calculate the density at thi...

Q: Derive Archimedes’ principle using a body of general shape.

Derive Archimedes’ principle using a body of general shape.

Q: Consider the isentropic flow through a supersonic wind-tunnel nozzle.

Consider the isentropic flow through a supersonic wind-tunnel nozzle. The reservoir properties are T0=500 K and p0=10 atm. If p=1 atm at the nozzle exit, calculate the exit temperature and density.

Q: Consider air at a pressure of 0.2 atm. Calculate

Consider air at a pressure of 0.2 atm. Calculate the values of τT and τs . Express your answer in SI units.

Q: Consider a point in a flow where the velocity and temperature are

Consider a point in a flow where the velocity and temperature are 1300 ft/s and 480 ◦R, respectively. Calculate the total enthalpy at this point.