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Analysis of Effect of Rolling Pull-Outs on Wing and Aileron Loads of a Fighter AirplaneAn analysis was made to determine the effect of rolling pull-out maneuvers on the wing and aileron loads of a typical fighter airplane, the P-47B. The results obtained indicate that higher loads are imposed upon wings and ailerons because of the rolling pull-out maneuver, than would be obtained by application of the loading requirements to which the airplane was designed. An increase of 102 lb or 15 percent of wing weight would be required if the wing were designed for rolling pull-out maneuver. It was also determined that the requirements by which the aileron was originally designed were inadequate.
Document ID
19930092725
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Wartime Report
Authors
Pearson, Henry A.
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Aiken, William S.
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 15, 2013
Publication Date
March 1, 1946
Subject Category
Aerodynamics
Report/Patent Number
NACA-WR-L-270
Accession Number
93R22015
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
AIRFOILS - NACA 65-410 - ORDINATES LOW-DRAG (BLOWER BLADE)
CHARTS - VANES, GUIDE
AIRFOILS - NACA 65-110 - ORDINATES LOW-DRAG (BLOWER BLADE)
AIRFOILS - CASCADES
AIRFOILS - NACA 65-(12)10 - ORDINATES LOW-DRAG (BLOWER BLADE)
AIRFOILS - NACA 65-810 - ORDINATES LOW-DRAG (BLOWER BLADE)
AIRFOILS - NACA 64-(A)06 - ORDINATES LOW-DRAG (BLOWER BLADE)
AIRFOILS - NACA 65-210 - ORDINATES LOW-DRAG (BLOWER BLADE)
FLOW - VANES, GUIDE
VANES, GUIDE
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