Question

Remaining Time: 1 hour, 59 minutes, 29 seconds. Question Completion Status: 1. Consider the following airfoil data: 0 80 Stedaro 224 12 Secrion irt cofficent, NACA 2412 Wing Beetion NACA 2412 Wing Section (centisund Notice that the arifoil data is shown at Reynold numbers from 3.1 to 8.9 million. The airfoil has a chord of 4 feet and is flying at 83.1 mph at sea level. 3. What are the (2-D) Ch Ca C .. at4 dearees AOA? Remaining Time: 1 hour, 59 minutes, 18 seconds. Question Completion Status: o 57 004 Stondor 5.7 1.6 1.2 -16 Section it coefficens, NACA 2412 Wing Betion NACA 2412 Wing Section (ontiurd Notice that the arifoil data is shown at Reynold numbers from 3.1 to 8.9 million. The airfoil has a chord of 4 feet and is flying at 83.1 mph at sea level. 2. What is the zero-lift angle? What are the (2-D) C Cd, Cm/4 at 4 degrees AOA? What is the (3-D) CL if the aircraft that is flying at the same velocity weighs 2,500 ibs and has a wing reference area of 100 sq.ft. If the wing span of this rectangular is 24.5 ft, and the lift distribution is ideal (elli critical Reynolds of 500,000 and use flat plate friction coefficients (gnore 2-D Cd data) 4. what is the total (3-D) drag coefficient? Assume a

Answer 1

Fo NACA 2412

で.Yad T2 一0912. 4 V4 4-

Sec SL S= 100 sg. 2. W 一 2x2500 L= 0.043 24.5 Re = SX10s From t tle Do= 0.06 2. O. 000098 G, = CO,tgi -0.0(+0.00009 8 = 0.06