Consider a constant density gas flowing steadily over an airfoil. Far upstream the velocity is V0. Halfway along the top surface
, the velocity has increased to 2V0. Halfway along the bottom surface, the velocity has decreased to V0/2. Find the pressure difference between the top and bottom surface at this location. State all your assumptions.
1 answer:
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Answer:
Explanation:
given data:
v_1 = 2.37 L
v_2 = 1.68 L
p_1 =1.15 atm
p_2 = ?
t_1 = 280 K
t_2 = 304 K
from Gas Law Equation
, WE HAVE
Putting the values