1. A uniform rigid wing section of span 1 m and chord 0.2 m is suspended...

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1. A uniform rigid wing section of span 1 m and chord 0.2 m is suspended in a wind-tunnel as shown below. For the wind tunnel, static pressure and air specific heat ratio is given as 40 kN/m and y = 1.4, respectively. For C=5.5/-M per radian, and 1 CMB = -0.25CLB" = U , calculate the aileron reversal Mach number. X = 0.1c K= 5.6 KN/m Cla X = 0.7c K = 4 KN/m 2. Using Excel or MATLAB, plot a family of curves that depicts the relationship of the aileron elastic efficiency, E, versus normalized dynamic pressure = q/qp, for various values of R=qR/9D and 0 1. You should make two plots on the following scales to reduce confusion: a) Plot R <1 using axes 3 1. A uniform rigid wing section of span 1 m and chord 0.2 m is suspended in a wind-tunnel as shown below. For the wind tunnel, static pressure and air specific heat ratio is given as 40 kN/m and y = 1.4, respectively. For C=5.5/-M per radian, and 1 CMB = -0.25CLB" = U , calculate the aileron reversal Mach number. X = 0.1c K= 5.6 KN/m Cla X = 0.7c K = 4 KN/m 2. Using Excel or MATLAB, plot a family of curves that depicts the relationship of the aileron elastic efficiency, E, versus normalized dynamic pressure = q/qp, for various values of R=qR/9D and 0 1. You should make two plots on the following scales to reduce confusion: a) Plot R <1 using axes 3