Can I get the solution for this? Thank you

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 CL2. 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 4.54 79.64 112.45 m/s deg. kph km 246.74 1.94 92.87 64.87 5.77 m/s km kph deg Minimum glide path angle Velocity at maximum flight time Maximum range O O (CL/CD) max Minimum Rate of Descent 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 CL2. 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 4.54 79.64 112.45 m/s deg. kph km 246.74 1.94 92.87 64.87 5.77 m/s km kph deg Minimum glide path angle Velocity at maximum flight time Maximum range O O (CL/CD) max Minimum Rate of Descent