b) Which airfoil is at a higher Reynolds number? How do you know? 1.5 CL 1.D...

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b) Which airfoil is at a higher Reynolds number? How do you know? 1.5 CL 1.D 0.5 0.0 -0.5 100 200 -0.100 10 CH -0.07 -0.02% 104 Co -0.0306 -5 300 -2 2 d 10 400 -0.5 Plot A 1.5 CL 1.D 0.5 D. D -0.5 -1.0 Plot A Plot B c) Which airfoil has a turbulent upper-surface boundary layer? How do you know? 300 0.-10- bum/ PA 6.2. 600 Plot B 900 10" - Co 1200 b) Which airfoil is at a higher Reynolds number? How do you know? 1.5 CL 1.D 0.5 0.0 -0.5 100 200 -0.100 10 CH -0.07 -0.02% 104 Co -0.0306 -5 300 -2 2 d 10 400 -0.5 Plot A 1.5 CL 1.D 0.5 D. D -0.5 -1.0 Plot A Plot B c) Which airfoil has a turbulent upper-surface boundary layer? How do you know? 300 0.-10- bum/ PA 6.2. 600 Plot B 900 10" - Co 1200