- #1
ra180
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Calculate the thickness of the boundary Layer δ at a location x= 0.3m along the chord length of an aircraft wing at each of the following velocities. (u = 20, 40,60,80,100 knots)
Assume ISA P=101325 R=287 T=288.5 μ =18 x 10-6
(1)Re transition=5 x 10^5
(2)δ Laminar = x 4.91 Rex^-0.5
(3)δ turbulent = x 0.381 Re^-0.2
Using Re= ρux/μ
Re(20) =21008 Re (40)= 420175 Re (60)=630262 Re (80)= 840350 Re (100)= 1050233
I'm not to sure where to go from here, do I have to substitute the Reynolds into the three equations if so which values do substitute.
Assume ISA P=101325 R=287 T=288.5 μ =18 x 10-6
(1)Re transition=5 x 10^5
(2)δ Laminar = x 4.91 Rex^-0.5
(3)δ turbulent = x 0.381 Re^-0.2
Using Re= ρux/μ
Re(20) =21008 Re (40)= 420175 Re (60)=630262 Re (80)= 840350 Re (100)= 1050233
I'm not to sure where to go from here, do I have to substitute the Reynolds into the three equations if so which values do substitute.