Problem 1:As shown in Fig. 1(a), a flat-plate airfoil with a chord length c has an angle of attack, a..Surface pressures on the lower and upper surfaces are p1 and p2, respectively.Calculate the lift and drag of the flat-plate airfoil.Note: Decompose pressure vectors into the vertical and horizontal components thatcontribute to the lift and drag, respectively.Problem 2:As shown in Fig. 1(b), a two-segment airfoil with a chord length c has a slope angle a..Surface pressures on the two upper surfaces are p1 and p3, respectively. The pressure onthe lower surface is p2.Calculate the lift and drag of the flat-plate airfoil.Note: Decompose pressure vectors into the vertical and horizontal components thatcontribute to the lift and drag, respectively. The chord length c is a distance between theleading and trailing edges. You need to calculate the length of a segment.a(a)plp2p2apl(b)p3

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Problem 1: As shown in Fig. 1(a), a flat-plate airfoil with a chord length c has an angle of attack, Surface pressures on the lower and upper surfaces are pl and p2, respectively. Calculate the lift and drag of the flat-plate airfoil. Note: Decompose pressure vectors into the vertical and horizontal components that contribute to the lift and drag, respectively.

Problem 1: As shown in Fig. 1(a), a flat-plate airfoil with a chord length c has an angle of attack, Surface pressures on the lower and upper surfaces are pl and p2, respectively. Calculate the lift and drag of the flat-plate airfoil. Note: Decompose pressure vectors into the vertical and horizontal components that contribute to the lift and drag, respectively.