Airfoil section characteristics as applied to the prediction of air forces and their distribution on wings (1938)
NASA Technical Reports Server (NTRS) · leaf 19
REPORT NO. 631—NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS 16 1. From CLb and equation (28) From this point, the distribution of forces and mo- GLu=l. 168X1.10-0.0507=1.233 ments on the upper wing are to be determined by using the method for finding the span load distribution given in appendix A.… … 100 O 20 40 60 80 Percent of affected tip distance 100 0 20 40 GO 80 -2 ~3 -5 Figure 19—Distribution of forces and moments on upper wing of biplane. 2. In order to reduce CLu to allow for the tip cor- rection, Fi and F2 are found from figure 17 ^=0.038 *W.06 Aspect ratio 5 6 i^Xi^O.040 The value of…
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