Aerospace Engineering Assignment

Problem 1 Estimate the drag force on the fuselage shown below for a cruising speed of 200 m/s at 10,000 m.

Problem 2 Estimate the required wing span for an aircraft of 10,000 kg, cruising at 300 m/s and 4,000 m. The wing may be approximated as a right triangle with chord length at the fuselage of 4 m and at the wing tip of 1.7 m with a NACA 0012 airfoil at 8 degree angle of attack.

Problem 3 Estimate the required thrust for the aircraft flying at 200 m/s at 7 km altitude as described below: Fuselage Length: 10 m Fuselage Cross-section: 2 m x 2 m Fuselage shape: parallelepiped Mass of fuselage, engine, vertical stabilizer, and payload: 8500 kg Wing Chord Length: 1 m Wing Shape: rectangle Wing weight per m of span: 500 kg/m Airfoil: NACA 4412 Angle of Attack: 10 degrees Vertical Stabilizer Height: 1.5 m Vertical Stabilizer base: 1 m Vertical Stabilizer shape: isosceles triangle