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The effect of lift, drag, and spinning characteristics of sharp leading edges on airplane wings / by Fred E. Weick and Nathan F. Scudder.
- Format:
- Book
- Government document
- Author/Creator:
- Weick, Fred E., author.
- Scudder, Nathan F., author.
- Series:
- Technical note (United States. National Advisory Committee for Aeronautics) ; 447.
- Technical note / National Advisory Committee for Aeronautics ; No. 447
- Language:
- English
- Subjects (All):
- Airplanes--Wings.
- Airplanes.
- Leading edges (Aerodynamics).
- Lift (Aerodynamics).
- Drag (Aerodynamics).
- Spin (Aerodynamics).
- Physical Description:
- 1 online resource (15 pages, 9 unnumbered pages) : illustrations.
- Place of Publication:
- Washington, [D.C.] : National Advisory Committee for Aeronautics, 1933.
- Summary:
- In the spin tests in flight, which were made on a small training biplane, the addition of sharp leading edges produced favorable effects, causing a decrease in the angle of attack and rate of rotation and making the controls more effective. The flight and wind-tunnel tests agreed in showing that the use of the sharp leading edges is accomplished by a substantial reduction in the maximum lift coefficient.
- Notes:
- Description based on online resource, PDF version; title from title page (TRAIL, viewed January 11, 2021).
- "February, 1933."
- "Langley Memorial Aeronautical Laboratory."
- "Part I - Wind-tunnel tests showing effect on lift, drag, and autorotation, by Fred E. Weick"--Pages 3-6.
- "Part II - Flight tests showing effect on the spin and performance of the XN2Y-1 airplane, by Nathan F. Scudder"--Pages 6-11.
- No Federal Depository Library Program (FDLP) item number.
- Includes bibliographical references (page 12).
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.
- Other Format:
- Print version: Weick, Fred E. The Effect of lift, drag, and spinning characteristics of sharp leading edges on airplane wings
- OCLC:
- 1143006540
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