4.11 The flying wing, B-2 stealth bomber can be approximated by a flat plate with dimensions of 69 f (chord) x 172 f (span). It’s cruising at 25,000 f. Assume the flow over both sides of the bomber is completely turbulent. The absolute viscosity coefficient is 5.2(10)-7 sl/f/s. Determine the total skin friction drag at Mach numbers 1.0, 2.0 and 3.0 for this airplane.
4.11 The flying wing, B-2 stealth bomber can be approximated by a flat plate with dimensions...
2. A recreational airplane has a rectangular wing of constant chord c 1.0m and spanb 10m which uses the same airfoil section from tip to tip. The lift curve slope of this airfoil is shown in the figure below. It is flying at the cruising speed of 50m/s through SSL ISA conditions. Assuming no 3D (finite span) effects (we will cover these in subsequent weeks), compute the following: (a) Cruising at sea level the angle of attack of the wing...