Question

If a glider needs to be flown at maximum range then, at which value of CL we should fly this glider? Consider CD0/K is 2.8.

(a) 1.67

(b) 3.2

(c) 5.6

(d) 2.5

I had been asked this question in class test.

Query is from Flight Mechanics in division Performance and Flight Mechanics of Aircraft Design

Answer 1

Right option is (a) 1.67

The best explanation: CL = [CD0/K] ^0.5 = 2.8^0.5 = 1.67.