Wind-tunnel investigation of ailerons on a low-drag airfoil. : 2 - The effect of thickened and beveled trailing edges / by Robert M. Crane and Ralph W. Holtzclaw.
An investigation was made in the Ames Aeronautical Laboratory 7- by 10-foot wind tunnel of the effects of a trailing edge of a 0.20-chord plain sealed aileron on an NACA 66,2-216 (a = 0.6) airfoil.
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| Other title: | NACA Wartime Reports. Series A. Technical report archive and image library. |
| 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. A54. |
| Subjects: |
MARC
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| 100 | 1 | |a Crane, Robert M. | |
| 245 | 1 | 0 | |a Wind-tunnel investigation of ailerons on a low-drag airfoil. : |b 2 - The effect of thickened and beveled trailing edges / |c by Robert M. Crane and Ralph W. Holtzclaw. |
| 246 | 3 | |a NACA Wartime Reports. Series A. | |
| 260 | |a Washington, D.C. : |b National Advisory Committee for Aeronautics, |c [1944] | ||
| 300 | |a 18 pages, 32 unnumbered pages : |b illustrations ; |c 27 cm. | ||
| 336 | |a text |b txt |2 rdacontent. | ||
| 337 | |a unmediated |b n |2 rdamedia. | ||
| 338 | |a volume |b nc |2 rdacarrier. | ||
| 490 | 1 | |a Wartime Report / National Advisory Committee for Aeronautics ; |v no. A54. | |
| 500 | |a NACA Wartime Report A-54. | ||
| 500 | |a Originally issued as NACA as Advance Confidential Report 4A15 (January 1944) | ||
| 500 | |a Prepared at the Ames Aeronautical Laboratory, Moffett Field, California. | ||
| 504 | |a Includes bibliographical references. | ||
| 520 | 3 | |a An investigation was made in the Ames Aeronautical Laboratory 7- by 10-foot wind tunnel of the effects of a trailing edge of a 0.20-chord plain sealed aileron on an NACA 66,2-216 (a = 0.6) airfoil. | |
| 520 | 3 | |a Thickening and beveling the trailing edge of the aileron was found to reduce the aileron effectiveness, reduce the slope of the wing section lift curve, and reduce the hinge-moment coefficients. These effects were maximum for the bevel, the length of which was 20 percent of the aileron chord, and decreased for both increasing and decreasing bevel lengths. Thickening and beveling the trailing edge caused an increase of 0.0001 in the minimum profile-drag coefficient. | |
| 583 | 1 | |a will digitize |c 20150604 |z Queued for digitization June 4, 2015 |2 pda |5 miu. | |
| 650 | 0 | |a Aerofoils. |0 http://id.loc.gov/authorities/subjects/sh85001301. | |
| 650 | 0 | |a Ailerons. |0 http://id.loc.gov/authorities/subjects/sh85002551. | |
| 650 | 0 | |a Trailing edges (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh2003006701. | |
| 650 | 0 | |a Drag (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh85039270. | |
| 650 | 0 | |a Wind tunnel testing. |0 http://id.loc.gov/authorities/subjects/sh2007008292. | |
| 650 | 7 | |a Aerofoils. |2 fast |0 (OCoLC)fst00798241. | |
| 650 | 7 | |a Ailerons. |2 fast |0 (OCoLC)fst00802020. | |
| 650 | 7 | |a Drag (Aerodynamics) |2 fast |0 (OCoLC)fst00897351. | |
| 650 | 7 | |a Trailing edges (Aerodynamics) |2 fast |0 (OCoLC)fst01154417. | |
| 650 | 7 | |a Wind tunnel testing. |2 fast |0 (OCoLC)fst01744047. | |
| 700 | 1 | |a Holtzclaw, Ralph W. | |
| 710 | 1 | |a United States. |b National Advisory Committee for Aeronautics. |0 http://id.loc.gov/authorities/names/n79060141 |1 http://isni.org/isni/0000000106642010. | |
| 710 | 2 | |a Ames Research Center. |0 http://id.loc.gov/authorities/names/n79138699 |1 http://isni.org/isni/0000000119557990. | |
| 730 | 0 | |a Technical report archive and image library. |0 http://id.loc.gov/authorities/names/no2008179973. | |
| 776 | 0 | 8 | |i Online version: |a Crane, Robert M. |t Wind-tunnel investigation of ailerons on a low-drag airfoil. |d Washington, D.C. : National Advisory Committee for Aeronautics, [1944] |w (OCoLC)937437520. |
| 830 | 0 | |a Wartime Reports (United States. National Advisory Committee for Aeronautics) ; |v no. A54. | |
| 856 | 4 | 2 | |u https://www.hathitrust.org/ |z Search for the full-text version of this title in HathiTrust |
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