Wind-tunnel investigation of control-surface characteristics. : 26 - Pressure distribution over an NACA 0009 airfoil with 0.30-airfoil-chord beveled-trailing-edge flaps /

Wind-tunnel investigation of control-surface characteristics. : 26 - Pressure distribution over an NACA 0009 airfoil with 0.30-airfoil-chord beveled-trailing-edge flaps / by H. Page Hoggard, Jr. and Marjorie E. Bulloch.

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Pressure-distribution tests have been made in the NACA 4- by 6-foot vertical tunnel of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. The flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The 15-percent be...

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Bibliographic Details
Main Author: Hoggard, H. Page
Corporate Authors: United States. National Advisory Committee for Aeronautics, Langley Aeronautical Laboratory
Other Authors: Bulloch, Marjorie E.
Other title:NACA Wartime Reports. Series L.
Format: Government Document Book
Language:English
Published: Washington, D.C. : National Advisory Committee for Aeronautics, [1944]
Series:Wartime Reports (United States. National Advisory Committee for Aeronautics) ; no. L205.
Subjects:
Aerofoils.
Airplanes > Control surfaces.
Flaps (Airplanes)
Trailing edges (Aerodynamics)
Aerodynamic load.
Hinge moments (Aerodynamics)
Wind tunnel testing.
Charts, diagrams, etc.

Norlin Library - Basement - Government Information - US

Holdings details from Norlin Library - Basement - Government Information - US
Call Number: Y 3.N 21/5:11/L205
Y 3.N 21/5:11/L205 Available Place a Hold

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