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Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes

Author: Marvin Pitkin; Bernard Maggin; United States. National Advisory Committee for Aeronautics.; Langley Aeronautical Laboratory.
Publisher: Washington, D.C. : NACA, 1944? 1945?
Series: Wartime reports, L-164.; Wartime Reports (United States. National Advisory Committee for Aeronautics), no. L164.
Edition/Format:   Print book : National government publication : EnglishView all editions and formats
Database:WorldCat
Summary:
An analysis has been made of factors affecting the net lift increment attainable with trailing-edge split flaps on tailless airplanes. The flaps investigated in the analysis were designed to contribute zero pitching moments about the wing aerodynamic center when deflected. Calculations were made of the lift and pitching-moment characteristics of flaps of this type over a range of design conditions in which sweepback  Read more...
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Additional Physical Format: Online version:
Pitkin, Marvin.
Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes.
Washington, D.C. : NACA, 1944? 1945?
(OCoLC)857368851
Material Type: Government publication, National government publication
Document Type: Book
All Authors / Contributors: Marvin Pitkin; Bernard Maggin; United States. National Advisory Committee for Aeronautics.; Langley Aeronautical Laboratory.
OCLC Number: 68838093
Notes: At head of title: National Advisory Committee for Aeronautics.
Caption title.
"Originally issued September 1944 as Advance restricted report L4118."
Description: 23 pages, 16 leaves : illustrations, charts ; 26 cm.
Series Title: Wartime reports, L-164.; Wartime Reports (United States. National Advisory Committee for Aeronautics), no. L164.
Responsibility: by Marvin Pitkin and Bernard Maggin.

Abstract:

An analysis has been made of factors affecting the net lift increment attainable with trailing-edge split flaps on tailless airplanes. The flaps investigated in the analysis were designed to contribute zero pitching moments about the wing aerodynamic center when deflected. Calculations were made of the lift and pitching-moment characteristics of flaps of this type over a range of design conditions in which sweepback angle, aspect ratio, taper ratio, flap chord, and flap deflection were widely varied. In addition, calculations were made to determine the effect of the various parameters upon the loss in lift incurred in trimming the stability moments of a tailless airplane. A method is given for roughly estimating the maximum lift coefficient of tailless airplanes.

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