Now consider a finite-span wing with the same profile, chord and attack angle flying at 5 km altitude with a speed of 50 m/s. Th
e wing aspect ratio is 5, area is 5 m2 , and span efficiency factor is 0.9. Determine the wing lift.
1 answer:
Answer:
Wing lift, L = 211.57kg
Explanation:
We are given:
•Attitude= 5Km
•V = 50m/s => 164.042 ft/s
• Area= 5m² = 53.8196ft²
•Aspect ratio = 5
•span efficiency factor = 0.9
Table is attached
For density at 5km, we have: d = 16404ft
To find wing lift, we use the formula:
Substituting figures, we have:
(1/2)*(0.0014314)*(164.042)²*(53.8196)*0.5*0.9
= 466.4382 lb
= 211.57
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