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Q.3 pts]An airfoil as shown in the figure will be used in a study in a wind tunnel where is located at all elevation of 500 m. The free stream velocity is set at 76 m/s. The airfoil chord length is [-0.2 m,and span length (normal to paper) is b-0.4 m. Calculate the airfoil (a) drag force, (b) lift force,(c) stagnation pressure at the airfoil nose. (d) If the airfoil is replaced with a thin flat plate (same 0.18length and b), what do you expect to happen to both drag Ua nd lift coefficients?

Fig: 1

Fig: 2