Question: Using the equations from thin aerofoil theory, evaluate the centre of pressure at angle of attack a = 5 for the aerofoil with the following

Using the equations from thin aerofoil theory, evaluate the centre of pressure at
angle of attack a=5 for the aerofoil with the following camber line
z(x)=0.5x(x 1), for 0<=x<=1
Use the theoretical value for the location of aerodynamic centre.

Step by Step Solution

There are 3 Steps involved in it

1 Expert Approved Answer
Step: 1 Unlock blur-text-image
Question Has Been Solved by an Expert!

Get step-by-step solutions from verified subject matter experts

Step: 2 Unlock
Step: 3 Unlock

Students Have Also Explored These Related Mechanical Engineering Questions!