Consider tests of an unswept wing that spans the wind tunnel and whose airfoil section is NACA 23012. Since the wing model spans
the test section, we will assume that the flow is two dimensional. The chord of the model is 1.3 m. The test section conditions simulate a density altitude of 3 km. The velocity in the test section is 360 km/h.
a. What is the lift per unit span (N/m) that you would expect to measure when the wing attack angle is 4°?
b. What would be the corresponding section lift coefficient and die moment coefficient (about the quarter-chord point)?
a. What is the lift per unit span (N/m) that you would expect to measure when the wing attack angle is 4°?
b. What would be the corresponding section lift coefficient and die moment coefficient (about the quarter-chord point)?
1 answer:
Answer:
Check the explanation
Explanation:
to know the lift per unit span (N/m) that is expected to be measured when the wing attack angle is 4°
as well as the corresponding section lift coefficient and die moment coefficient .
Kindly check the attached image below to see the step by step explanation to the above question.
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Answer:
51.4 Ohms
Explanation:
By applying voltage division rule
where v is voltage, subscripts i and f represnt initial and final, R is resistance, m is internal and l is external.Substituting 7V for final voltage, 10V for initial voltage and the external resistance as 120 Ohms then