In a wind tunnel test, a 3D tapered wing has span b = 0.9 m, chord cr=0.18 m and c = 0.06 m, as shown in Figure 4a. The

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In A Wind Tunnel Test A 3d Tapered Wing Has Span B 0 9 M Chord Cr 0 18 M And C 0 06 M As Shown In Figure 4a The 1 (51.37 KiB) Viewed 11 times

In a wind tunnel test, a 3D tapered wing has span b = 0.9 m, chord cr=0.18 m and c = 0.06 m, as shown in Figure 4a. The airfoil NACA4415 has negative attack angle at zero lift az-o = -5°. At geometrical attack angle of 10° and Reynolds number of 1,000,000, the moment coefficient about LE is found to be -0.05. The induced drag factor is plotted in Figure 4b. 0.16 0.12 8 0.08 AR-10 0.04 b 0.005 0 0.4 0.6 0.8 1.0 C/C, Figure 4b Figure 4a (a) Predict the lift coefficient at a= 10° by the potential theory of 2D thin airfoil. (3 marks) (b) Locate the centre of pressure on the chord line in part (a). (2 marks) (c) Determine the reduced lift coefficient and induced drag coefficient of the 3D wing. (9 marks) (d) Determine the lift force on the 3D wing at the flight speed corresponding to the given Reynolds number. (5 marks) | (2) Express the three equations for conservation of momentum, energy, and ideal air, in terms of p, P, V and T along a streamline in the compressible and adiabatic air flow. (6 marks)