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My source is STUDIES OF HIGH LIFT/DRAG RATIO HYPERSONIC CONFIGURATIONS by John V. Becker, to be found online here. It is from 1964, so more than 50 years old, but since a lot of research had been performed already before that date, it might still be relevant. In short: It depends. On thickness ratio and Reynolds number, for example, as can be seen in this ...


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You could argue for one or for both, but ultimately, it doesn't matter - as long as you are consistent and use the same reference area throughout your calculation/analysis. If I personally were to choose, I would go for both, on the basis of total lifting area. EDIT for details ------ Well yet again, it doesn't matter. You will get some value for your $C_{...


1

Curiously, when we plug some numbers, L/D comparison of the "waverider" get better and better as Mach increases: M $\frac{4 \cdot (M+3)}{M}$ $\frac{6 \cdot (M+2)}{M}$ 1 16 18 2 10 12 3 8 10 4 7 9 5 6.4 8.4 This confirms that supersonic aircraft do better as "bottom lifters", essentially an extrapolation of supercritical wing design....


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