20 points A 200-kg experimental glider with a semi-span of 7 m and chord of 1m (rectangular wing) was released at a standard altitude where the temperature is 240 K. The drag polar equation of the glider is predetermined to be CD = 0.0351 +0.0449 CL?. Assume no wing loading and density changes during the glide. Also, assume acceleration due to gravity is constant at 9.8066 m/s. (4 pts. each) 1.65 m/s 4.54 deg. 79.64 112.45 kph km 246.74 1.94 m/s 92.87 km 64.87 kph 5.77 deg. 1 (CLP/CD2) max Maximum range Minimum glide path angle O O O O Minimum Rate of Descent Velocity at maximum O flight time O O O O