Theoretical stability and control characteristics of wings with various amounts of taper and twist (1938)
NASA Technical Reports Server (NTRS) · leaf 12
e the value of this moment rb but also to make it slightly negative for low wing lift Lya«ta,=Git^yqSb (10) coefficients. By the process described in the previous section, values As was the case with and C*,, the value of C,r of Ctr may be obtained for wings with any initial twist for the entire… … O .2 .4 .6 .8 W Extent of flap from iv/ng center A part of the wing yawing moment due to yawing (a) A=6. results from the change in the induced-drag distribution (b) .4=10. (c) A=16. that accompanies the change in the lift distribution Figure 12.—Yawing derivative duo to yawing for partial-span…
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