1. Fuselagealone 0 lPl 66'. 6 =Ip 0 7P1669,6= Z0 a 7P1660,6 = 5'
2. wing configuration at M = 1.80. increase i n lift coefficient and So of fuselage incidence produces approximately a U.075 increase i n lift coefficient. However, the data for the fuselage alone show that the fuselage i s actually carrying only 33 percent of the total configuration lift. In particular, at an angle of attack of 2', the fuselage has a lift coefficient of 0.01. compared to a value of 0.03 for the complete configuration, and by extrapolating the data to 5" angle of attack, the fuselage i s expected to have a lift coefficient of 0.03 compared t o a value of 0.075 for the complete configuration. Based upon the data of figures 6-9, it can be concluded that inclining the fuselage at a positive incidence does improve the lifting Characteristics of a highly swept wing.
3. fuselage at M c 1-80.