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Tests on airplane fuselages, floats and hulls (1927)
NASA Technical Reports Server (NTRS) · leaf 16
145 TESTS OS AIRPLANE FUSELAGES, FLOATS AND HULLS F4 £3 0°pitch andyav/ S'=.0739 sq.fi. 0°pitch and yaw S=.07S/ sg. ft. V, f.pjs. 44.0 58.7 73.3 83.0 Y, f.p.s. 44.0 58.7 73.3 88.0 D,lb. .0423 .0730 .1133 .1613 D,lb. .0339 .0598 .0333 .1318 DIS, lhlsg.fi. .5633 .9587 1.5033 3.1478 B/S, Ib./sq.ff.… … °Q' 4' 8' ia> 16' 20' O" 4' 8° IE" 16' Angle of pitch, (deck line) Angle of pitch,(keel line} Drag on Sopwith seaplane float. F=88 f. p. s. (Ref. Drag oaN-9 seaplane float. F=SSf.p.s. (Kef. W. T. E. No. 147) W. T. R. No. 147) FB -3.937- Section X-X 0°pitch and yaw S=.2326 sq. ft. Q°'pitch andyaw…NASA Technical Reports Server (NTRS)
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