9Aerodynamics of Cambered Wings
Chapters 7 and 8 were intended primarily to explore the basic shapes of the main components and full‐airplane configurations offering the promise of high aerodynamic efficiency. Essential characteristics affecting the drag appeared to be the longitudinal volume distribution and the slenderness ratio of the fuselage, the wing thickness ratio, the leading edge sweep angle and the notch ratio. However, this enumeration is arbitrary in the sense that the feasibility of a new SCV configuration is not only determined by its properties in the high‐speed cruise condition but also in off‐design conditions such as taking‐off, subsonic climb and descent, and landing.
The present chapter is intended to give an overview of possibilities to improve the aerodynamic shape of thin wings by applying camber in longitudinal and lateral directions. In particular, reference is made to Figure 7.1, where the possibility of realizing a high percentage of the theoretical maximum leading edge suction is mentioned.
Figure 9.1 Basic drag subdivision at supersonic speeds.
The introduction into the analysis of drag in cruising flight in Chapter 7 is used to make an initial estimate of the aerodynamic efficiency of an SCV in supersonic cruising flight. Figure 9.1 depicts the components of airframe drag at supersonic speeds contributions breakdown of drag components, which ...
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