Figure 9.13. Dissected aircraft components

author does not recommend undertaking coursework on exotic-aircraft configurations unless the results can be substantiated. Learning with a familiar design that can be substantiated gives confidence to practitioners. Those in the industry are fortunate to have access to more accurate in-house data.

9.18 Coursework Example: Civil Bizjet Aircraft

The discussion on subsonic aircraft continues linearly from previous chapters.

9.18.1 Geometric and Performance Data

The geometric and performance parameters discussed herein were used in previous chapters. Figure 9.13 illustrates the dissected anatomy of the coursework baseline aircraft.

Aircraft cruise performance for the basic drag polar is computed as follows:

cruise altitude = 40,000 ft

LRC Mach = 0.65 (630 ft/s)

ambient pressure = 391.68 lb/ft2

ambient temperature = 390 K

ambient density = 0.00058 sl/ft3

ambient viscosity = 2.96909847 × 10−7lbs/ft2

Re/ft = 1.2415272 × 106 (use the incompressible zero Mach line, as explained in Section 9.7.1)

CL at LRC (Mach 0.65) = 0.5

CL at HSC (Mach 0.7) = 0.43

Fuselage (see Figure 9.13)

fuselage length, Lf = 15.24 m (50 ft)

average diameter at the constant cross-section barrel, Df = 1.75 m (5.74 ft)