c) To allow best performance, the installed wing should be configured to minimise the drag-to-lift-ratio. Evaluate drag coefficient Cp, lift coefficient C₁ and angle of attack a for the optimum set-up.
c) To allow best performance, the installed wing should be configured to minimise the drag-to-lift-ratio. Evaluate drag coefficient Cp, lift coefficient C₁ and angle of attack a for the optimum set-up.
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Can you just do part C please thanks. Just part C thanks
Transcribed Image Text:18. A new wing is going to be installed on an aircraft. The span of the wing is b = 6.0
m, while the chord length is c = 0.5 m. From wind tunnel experiments on a similar
wing with a different aspect ratio of A₁ = 6, but the same aerofoil profile as the wing
to be mounted, the following data sets are known;
{a +7.0 deg, CL
=
=
= +0.555, CD =
0.0290}
{a-1.5 deg, CL = -0.199, CD = 0.0121}
a) Evaluate the lift slope dc₁/da of the infinite wing (i.e. aerofoil profile)?
b) Evaluate the zero lift angle of attack ao and the drag coefficient ca of the infinite
wing.
c) To allow best performance, the installed wing should be configured to minimise
the drag-to-lift-ratio. Evaluate drag coefficient CD, lift coefficient CL and angle of
attack a for the optimum set-up.
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