Time-vector Determined Lateral Derivatives of a Swept-wing Fighter-type Airplane with Three Different Vertical Tails at Mach Numbers Between 0.70 and 1.48 (1956)
NASA Technical Reports Server (NTRS) · leaf 55
(a) M = 0.80. (b) M = 1.20. Figure 13.- Influence of Cnp and Clr on "the lateral stability derivatives for configuration C VJ1 ui at M = 0.80 and M = 1.20 at hp = 40,000 feet. Solution based on data obtained from faired curves.
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