Wind-tunnel tests of ailerons at various speeds. : 3 - Ailerons of 0.20 airfoil chord and true contour with 0.35-aileron-chord Frise balance on the NACA 23012 airfoil / by W. Letko and W.B. Kemp.
Hinge moment, lift, and pressure-distribution measurements were made on a Frise aileron on an NACA 23012 airfoil in the two-dimensional test section of the LMAL stability tunnel. Speeds up to 360 miles per hour corresponding to a Mach number of about 0.470 were used. The nose radius of the aileron w...
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| Corporate Authors: | , |
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| Other title: | NACA Wartime Reports. Series L. |
| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
[1943]
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| Series: | Wartime Reports (United States. National Advisory Committee for Aeronautics) ;
no. L325. |
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| Summary: | Hinge moment, lift, and pressure-distribution measurements were made on a Frise aileron on an NACA 23012 airfoil in the two-dimensional test section of the LMAL stability tunnel. Speeds up to 360 miles per hour corresponding to a Mach number of about 0.470 were used. The nose radius of the aileron was varied from 0.0012 to 0.0150 of the airfoil chord. Tests also were made with an increased vent gap and with the lower surface of the airfoil at the entrance of the slot rounded to a radius of 0.02 of the airfoil chord. The primary purpose of all tests was to determine the effects of speed on this type of aileron. |
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| Item Description: | NACA Wartime Report L-325. Originally issued as NACA as Advance Confidential Report L3I14 (September 1943) Prepared at the Langley Memorial Aeronautical Laboratory, Langley Field, Virginia. |
| Physical Description: | 12 pages, 20 unnumbered pages : illustrations ; 27 cm. |
| Bibliography: | Includes bibliographical references. |