Wind-tunnel investigation of control-surface characteristics. : 20 - Plain and balanced flaps on an NACA 0009 rectangular semispan tail surface / by I. Elizabeth Garner.
Correlation is established between aerodynamic characteristics of control surfaces in two-dimensional and three-dimensional flow. Slope of lift curve was affected little by overhang and balance-nose shape, but increased by sealing flap-nose gap. Effectiveness of balancing tab was same for sealed pla...
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| Main Author: | |
|---|---|
| Corporate Authors: | , |
| 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. L186. |
| Subjects: |
MARC
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| 100 | 1 | |a Garner, I. Elizabeth. |0 http://id.loc.gov/authorities/names/no2007060726. | |
| 245 | 1 | 0 | |a Wind-tunnel investigation of control-surface characteristics. : |b 20 - Plain and balanced flaps on an NACA 0009 rectangular semispan tail surface / |c by I. Elizabeth Garner. |
| 246 | 3 | |a NACA Wartime Reports. Series L. | |
| 260 | |a Washington, D.C. : |b National Advisory Committee for Aeronautics, |c [1944] | ||
| 300 | |a 16 pages, 41 unnumbered pages : |b illustrations, tables ; |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. L186. | |
| 500 | |a NACA Wartime Report L-186. | ||
| 500 | |a Originally issued as NACA as Advance Restricted Report L4I11f (October 1944) | ||
| 500 | |a Prepared at the Langley Memorial Aeronautical Laboratory, Langley Field, Virginia. | ||
| 504 | |a Includes bibliographical references. | ||
| 520 | 3 | |a Correlation is established between aerodynamic characteristics of control surfaces in two-dimensional and three-dimensional flow. Slope of lift curve was affected little by overhang and balance-nose shape, but increased by sealing flap-nose gap. Effectiveness of balancing tab was same for sealed plain flap and unsealed overhang flap. Changes in hinge-moment coefficient were diminished by sealing gap. Values measured by three-dimensional flow disagreed with two-dimensional flow values until aspect ratio corrections were made. | |
| 650 | 0 | |a Airplanes |x Tail surfaces. |0 http://id.loc.gov/authorities/subjects/sh85002903. | |
| 650 | 0 | |a Airplanes |x Control surfaces. |0 http://id.loc.gov/authorities/subjects/sh85002798. | |
| 650 | 0 | |a Flaps (Airplanes) |0 http://id.loc.gov/authorities/subjects/sh85049001. | |
| 650 | 0 | |a Air flow. |0 http://id.loc.gov/authorities/subjects/sh85002635. | |
| 650 | 0 | |a Hinge moments (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh85060958. | |
| 650 | 0 | |a Wind tunnel testing. |0 http://id.loc.gov/authorities/subjects/sh2007008292. | |
| 650 | 0 | |a Charts, diagrams, etc. |0 http://id.loc.gov/authorities/subjects/sh87002373. | |
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| 650 | 7 | |a Airplanes |x Control surfaces. |2 fast |0 (OCoLC)fst00803108. | |
| 650 | 7 | |a Airplanes |x Tail surfaces. |2 fast |0 (OCoLC)fst00803481. | |
| 650 | 7 | |a Charts, diagrams, etc. |2 fast |0 (OCoLC)fst00852545. | |
| 650 | 7 | |a Flaps (Airplanes) |2 fast |0 (OCoLC)fst00927038. | |
| 650 | 7 | |a Hinge moments (Aerodynamics) |2 fast |0 (OCoLC)fst00957213. | |
| 650 | 7 | |a Wind tunnel testing. |2 fast |0 (OCoLC)fst01744047. | |
| 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 Langley Aeronautical Laboratory. |0 http://id.loc.gov/authorities/names/n81018841. | |
| 830 | 0 | |a Wartime Reports (United States. National Advisory Committee for Aeronautics) ; |v no. L186. | |
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