Question

Consider a wing mounted in the test-section of a subsonic wind tunnel. The velocity of the airflow is 160 ft/s, and the velocity at a point on the wing is 293 ft/s.
If the test-section air temperature is 510°R and the flow velocity is increased to 450 ft/s, what is the pressure coefficient at the same point?


(Round the final answer to three decimal places.)

Answer 1

Answer:

A) To find the coefficient of pressure we will use

$PC=1-(\frac{V}{v_{\alpha } } )^2$

where

$V=293 ft/s\\v_{\alpha } =160ft/s$

insert values

$PC=1-(293/160)^2=-2.353$