Questions from Fundamentals of Aerodynamics

Q: Consider a subsonic compressible flow in cartesian coordinates where the velocity potential

Consider a subsonic compressible flow in cartesian coordinates where the velocity potential is given by If the freestream properties are given by V∞ = 700 ft/s, p∞...

Q: Using the Prandtl-Glauert rule, calculate the lift coefficient for

Using the Prandtl-Glauert rule, calculate the lift coefficient for an NACA 2412 airfoil at 5◦ angle of attack in a Mach 0.6 freestream. (Refer to Figure 4.5 for the original airfoil data.)

Q: Under low-speed incompressible flow conditions, the pressure coefficient at

Under low-speed incompressible flow conditions, the pressure coefficient at a given point on an airfoil is -0.54. Calculate Cp at this point when the freestream Mach number is 0.58, using a. The Prand...

Q: In low-speed incompressible flow, the peak pressure coefficient (

In low-speed incompressible flow, the peak pressure coefficient (at the minimum pressure point) on an airfoil is-0.41. Estimate the critical Mach number for this airfoil, using the Prandtl-Glauert rul...

Q: For a given airfoil, the critical Mach number is 0.

For a given airfoil, the critical Mach number is 0.8. Calculate the value of p/ p∞ at the minimum pressure point when M∞ = 0.8.

Q: Consider an airfoil in a Mach 0.5 freestream. At

Consider an airfoil in a Mach 0.5 freestream. At a given point on the airfoil, the local Mach number is 0.86. Using the compressible flow tables at the back of this book, calculate the pressure coeffi...

Q: Figure 11.5 shows four cases for the flow over the

Figure 11.5 shows four cases for the flow over the same airfoil wherein M∞ is progressively increased from 0.3 to Mcr=0.61. Have you wondered where the numbers on Figure 11.5 came from? Here is your c...

Q: Consider a flow field in polar coordinates, where the stream function

Consider a flow field in polar coordinates, where the stream function is given as ψ =ψ(r,θ). Starting with the concept of mass flow between two streamlines, derive Equations (2.148a and b).

Q: Consider the flow over a circular cylinder; the incompressible flow over

Consider the flow over a circular cylinder; the incompressible flow over such a cylinder is discussed in Section 3.13. Consider also the flow over a sphere; the incompressible flow over a sphere is de...

Q: In Problem 11.8, the critical Mach number for a

In Problem 11.8, the critical Mach number for a circular cylinder is given as Mcr=0.404. This value is based on experimental measurements, and therefore is considered reasonably accurate. Calculate Mc...