- #1
ChimM
- 17
- 0
Homework Statement
When Cl = 0.9, find the difference in induced drag for a rectangular wing of 36-ft. span and 6-ft. chord and a tapered wing of the same area, the tapered wing having a 6-ft. chord at the root, the leading and trailing edges being tangent to a circle of 2-ft. radius at the tip, and the fuselage being 3 ft. wide. The airspeed is 100 miles
per hour.
---From that question, I have been able to calculate the induced drag for the rectangular wing. How can I solve the average chord of the tapered wing by this,"the tapered wing having a 6-ft. chord at the root, the leading and trailing edges being tangent to a circle of 2-ft. radius at the tip, and the fuselage being 3 ft. wide".
Please help.. Thank you.