Span load distributions resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration for tapered sweptback wings with streamwise tips. : Subsonic leading edges and supersonic trailing edges / Margery E. Hannah and Kenneth Margolis.
On the basis of the linearized supersonic-flow theory and theoretical spanwise distributions of circulation (which are proportional to the span load distribution) resulting from constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips, subson...
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1952.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
2831. |
| Subjects: |
MARC
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| 100 | 1 | |a Hannah, Margery E. | |
| 245 | 1 | 0 | |a Span load distributions resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration for tapered sweptback wings with streamwise tips. : |b Subsonic leading edges and supersonic trailing edges / |c Margery E. Hannah and Kenneth Margolis. |
| 260 | |a Washington, D.C. : |b National Advisory Committee for Aeronautics, |c 1952. | ||
| 300 | |a 221 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. 2831. | |
| 500 | |a "December 1952." | ||
| 500 | |a NACA TN Number 2831. | ||
| 504 | |a Includes bibliographical references. | ||
| 520 | 3 | |a On the basis of the linearized supersonic-flow theory and theoretical spanwise distributions of circulation (which are proportional to the span load distribution) resulting from constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips, subsonic leading edges, and supersonic trailing edges. The results of the analysis are presented as a series of design charts. Some illustrative variations of the spanwise distributions of circulation with aspect ratio, taper ratio, Mach number, leading-edge sweepback, and axis-of-pitch location are also included. | |
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| 650 | 0 | |a Airplanes |x Wings, Swept-back. |0 http://id.loc.gov/authorities/subjects/sh85002928. | |
| 650 | 0 | |a Angle of attack (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh95010977. | |
| 650 | 0 | |a Aerodynamic load. |0 http://id.loc.gov/authorities/subjects/sh85001292. | |
| 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 | 0 | |a Rolling (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh85114890. | |
| 650 | 0 | |a Pitching (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh85102496. | |
| 650 | 0 | |a Aerodynamics, Supersonic. |0 http://id.loc.gov/authorities/subjects/sh85001297. | |
| 700 | 1 | |a Margolis, Kenneth. |0 http://id.loc.gov/authorities/names/nr2004026901 |1 http://isni.org/isni/0000000053168668. | |
| 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 2831. |0 http://id.loc.gov/authorities/names/no2009017392. | |
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