Theoretical supersonic characteristics of inboard trailing-edge flaps having arbitrary sweep and taper. : Mach lines behnid flap leading and trailing edges / Julian H. Kainer and Jack E. Marte.
Generalized expressions in closed form have obtained by means of linearized theory for the aerodynamic characteristics (lift-, rolling-moment-, pitching-moment-, and hinge-moment-coefficient derivatives) due to deflection of inboard trailing-edge flaps. The analysis considers the effects of Mach num...
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| Corporate Author: | |
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1950.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
2205. |
| Subjects: |
MARC
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| 100 | 1 | |a Kainer, Julian H. | |
| 245 | 1 | 0 | |a Theoretical supersonic characteristics of inboard trailing-edge flaps having arbitrary sweep and taper. : |b Mach lines behnid flap leading and trailing edges / |c Julian H. Kainer and Jack E. Marte. |
| 260 | |a Washington, D.C. : |b National Advisory Committee for Aeronautics, |c 1950. | ||
| 300 | |a 39 pages : |b illustrations ; |c 28 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 National Advisory Committee for Aeronautics. Technical Note ; |v no. 2205. | |
| 500 | |a "October 1950." | ||
| 500 | |a NACA TN Number 2205. | ||
| 504 | |a Includes bibliographical references. | ||
| 520 | 3 | |a Generalized expressions in closed form have obtained by means of linearized theory for the aerodynamic characteristics (lift-, rolling-moment-, pitching-moment-, and hinge-moment-coefficient derivatives) due to deflection of inboard trailing-edge flaps. The analysis considers the effects of Mach number and flap aspect ratio, taper ratio, and sweep for the conditions where the Mach lines lie behind the flap leading and trailing edges. The flap configurations analyzed are limited to the case of streamwise tips where the foremost Mach lines from the flap tips do not intersect the root and tip chords of the wing. | |
| 583 | 1 | |a committed to retain |c 20230101 |d 20480101 |5 CoU |f Alliance Shared Trust |u https://www.coalliance.org/shared-print-archiving-policies. | |
| 650 | 0 | |a Flaps (Airplanes) |0 http://id.loc.gov/authorities/subjects/sh85049001. | |
| 650 | 0 | |a Aerodynamics, Supersonic. |0 http://id.loc.gov/authorities/subjects/sh85001297. | |
| 650 | 0 | |a Leading edges (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh85075483. | |
| 650 | 0 | |a Trailing edges (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh2003006701. | |
| 650 | 7 | |a Aerodynamics, Supersonic. |2 fast |0 (OCoLC)fst00798221. | |
| 650 | 7 | |a Flaps (Airplanes) |2 fast |0 (OCoLC)fst00927038. | |
| 650 | 7 | |a Leading edges (Aerodynamics) |2 fast |0 (OCoLC)fst00994749. | |
| 650 | 7 | |a Trailing edges (Aerodynamics) |2 fast |0 (OCoLC)fst01154417. | |
| 700 | 1 | |a Marte, Jack E. | |
| 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. | |
| 830 | 0 | |a Technical note (United States. National Advisory Committee for Aeronautics) ; |v 2205. |0 http://id.loc.gov/authorities/names/no2009017392. | |
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