An approximate analytical method for studying entry into planetary atmospheres / Dean R. Chapman.
The pair of motion equations for entry into an exponential planetary atmosphere is reduced to a single, ordinary, nonlinear differential equation of second order by disregarding two relatively small terms and by introducing a certain mathematical transformation. The reduced equation includes various...
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| Main Author: | |
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington :
National Advisory Committee for Aeronautics,
[1958]
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
4276. |
| Subjects: |
MARC
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| 100 | 1 | |a Chapman, Dean R. |0 http://id.loc.gov/authorities/names/no2007062998. | |
| 245 | 1 | 3 | |a An approximate analytical method for studying entry into planetary atmospheres / |c Dean R. Chapman. |
| 260 | |a Washington : |b National Advisory Committee for Aeronautics, |c [1958] | ||
| 300 | |a 2 unnumbered pages, 101 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 Technical note / National Advisory Committee for Aeronautics ; |v 4276. | |
| 500 | |a "May 1958." | ||
| 500 | |a NACA TN Number 4276. | ||
| 504 | |a Includes bibliographical references. | ||
| 520 | 3 | |a The pair of motion equations for entry into an exponential planetary atmosphere is reduced to a single, ordinary, nonlinear differential equation of second order by disregarding two relatively small terms and by introducing a certain mathematical transformation. The reduced equation includes various terms, certain of which represent the gravity force, the centrifugal acceleration, and the lift force. If these particular terms are disregarded, the differential equation is linear and yields precisely the solution of Allen and Eggers applicable to ballistic entry at relatively steep angles of descent. If all the other terms in the basic equation are disregarded (corresponding to negligible vertical acceleration and negligible vertical component of drag force), the resulting truncated differential equation yields the solution of Sanger for equilibrium flight of glide vehicles with relatively large lift-drag ratios. | |
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| 650 | 0 | |a Space vehicles |x Atmospheric braking. |0 http://id.loc.gov/authorities/subjects/sh2002010133. | |
| 650 | 0 | |a Mathematical analysis. |0 http://id.loc.gov/authorities/subjects/sh85082116. | |
| 650 | 0 | |a Differential equations. |0 http://id.loc.gov/authorities/subjects/sh85037890. | |
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| 650 | 7 | |a Space vehicles |x Atmospheric entry. |2 fast |0 (OCoLC)fst01127959. | |
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| 830 | 0 | |a Technical note (United States. National Advisory Committee for Aeronautics) ; |v 4276. |0 http://id.loc.gov/authorities/names/no2009017392. | |
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