Calculate the elevator deflection angle necessary to trim the configuration at an angle of attack of8°.

Consider the configuration of Prob. 7.7. The elevator hinge moment derivatives are Assess the stick-free static stability of this configuration. Prob. 7.7. Assume that an elevator is added to the horizontal tail of the configuration given in Pro b. 7 .4. The elevator control effectiveness is 0.04. Calculate the elevator deflection angle necessary to trim the configuration at an angle of attack of8°. Prob. 7.4. Consider the wing-body model in Prob. 7.2. Assume that a horizontal tail with no elevator is added to this model. The distance from the airplane’s center of gravity to the tail’s aerodynamic center is 1.0 m. The area of the tail is 0.4 nr, and the tail-setting angle is 2.0°. The lift slope of the tail is 0.12 per degree. From experimental measurement, .lf the absolute angle of attack of the model is 5° and the lift at this angle ·of attack is 4134 N, calculate the moment about the center of gravity. Prob. 7.2. Consider a model of a wing-body shape mounted in a wind tunnel. The flow conditions in the test section are standard sea-level properties with a velocity of 100 . The wing area and chord are 1.5 m2 and 0.45 m, respectively. Using the wind tunnel force and moment-measuring balance, the moment about the center of gravity when the lift is zero is found to be -12.4 N · m. When the model is pitched to another angle of attack, the lift and moment about the center of gravity are measured to be 3675 20.67 N · m, respectively. Calculate the value of the moment coefficient about the aerodynamic center and the location of the aerodynamic center.


 

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