1. Determine the equivalent parasite drag area (f) of your
fuselage at the Reynolds number and Mach number associated with the design
cruise condition. (Express the answer in ft2 or m2). Include the drag associated with fuselage upsweep using the method in the notes. If your design is supersonic, also include an estimate of the volume-dependent wave drag.
2. Neglecting compressibility drag, determine equations for
a. the lift coefficient for maximum lift to drag ratio, (L/D)max
b. the value of (L/D)max
Express the answers in terms of AR, e, and CDp. Also express the formula for L/Dmax in terms of b, f, and e. (Note: no numbers here, just a quick analytical derivation is needed.)
Extra credit: Changing the seating arrangement changes the fuselage drag
through changes in wetted area, fineness ratio, and Reynolds number.
Investigate the effect of seat spacing (number of seats abreast, number of
aisles, seat pitch, etc.) on the overall fuselage drag (ffuselage)
and wetted area.