The measurements were made at various angles of pitch but at zero angle of roll and yaw, the wing chord being set at an angle of + 4 ยฐ to, the fuselage axis. In the case of the Clark Y airfoil the measurements have been extended to a pitch angle of 4 oยฐ, using ailerons of span equal to 67 per cent.
โฆ LIBER โฆ
Report No. 349. A proof of the theorem regarding the distribution of lift over the span, for minimum induced drag: By W. F. Durand. 15 pages, illustrations, quarto. Washington, Government Printing Office, 1930. Price ten cents
- Publisher
- Elsevier Science
- Year
- 1930
- Tongue
- English
- Weight
- 86 KB
- Volume
- 210
- Category
- Article
- ISSN
- 0016-0032
No coin nor oath required. For personal study only.
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## BOOK REVIEWS. I29 of repeated networks and some generalizations of "[" and II sections. The remaining chapters are concerned chiefly with extensions or applications. They include such subjects as Filters, Homographic Transformation, Coil Loaded Telephone Cable and Multistage Amplifier. The boo