A study of factors affecting the steady spin of an airplane (1933)
NASA Technical Reports Server (NTRS) · leaf 25
N.A.C.A. Technical Note No.468 Figs. 7,8,9 Figure 7.- Angle of attack at wing tips computed for NY-1 spin- ning conditions with elevator up 33° 10 20 30 40 50 60 70 80 Angle of attack at center section, degrees … -2Cr 0 20 40 60 80 100 Angle of attack, degrees 1.6 Figure 9.- o Normal and 1.2 chord-force L coef fic ients for G5t t ingen .8 398 airfoil wi thout and with sharp leading edge. .4 lv (From refer- ence 5.) 1 0 -.41 10 20 30 40 50 60 70 80 -10 Angle of attack, degrees
NASA Technical Reports Server (NTRS)
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