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Force and Pressure-Distribution Measurements on a Rectangular Wing with Double-Hinged NoseThe previous measurements on airfoils with hinged nose disclosed a comparatively large low-pressure peak at the bend of the hinged nose; which favored the separation of flow. It was therefore attempted to reduce these low-pressure peaks by reducing the camber of the forward profile and thereby ensure a longer adherence of the flow and a maximum lift increase. The forces were measured on a rectangular wing with double-hinged nose and end plates, the pressure distributions were measured in the center section of the wing. The measurements disclosed that the highest lift attained with a single-hinged nose cannot be increased by a double-hinged nose. The sum of the deflection angles of both hinged noses related to the maximum lift is about equal to the corresponding angle of the single-hinge nose (approx. 30 deg to 40). The respective angle of attack in both cases amounts to approx. 21 deg. Even the low-pressure peak is about the same in both cases (P/q approx. -5.5). Therefore, a milder curvature of the forward portion of the profile affords no definite increase of the maximum lift.
Document ID
20050019455
Acquisition Source
Langley Research Center
Document Type
Other - NACA Technical Memorandum
Authors
Lemme, H. A. (Zentrale fuer Wissenschaftliches Berichtswesen Berlin, Germany)
Date Acquired
August 22, 2013
Publication Date
March 1, 1947
Publication Information
Publication: Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluft-zeugmeisters
Subject Category
Aerodynamics
Report/Patent Number
NACA-TM-1117
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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