Calculated effects of body shape on the bow-shock overpressures in the far field of bodies in supersonic flow / by Donald L. Lansing.
The theory developed by G.B. Whitham (Communications on Pure and Applied Mathematics, August 1952) for the supersonic flow about bodies in uniform flight in a homogeneous medium is reviewed and an integral which expresses the effect of body shape upon the flow parameters in the far field is reduced...
Saved in:
| Main Author: | |
|---|---|
| Corporate Authors: | , |
| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Aeronautics and Space Administration,
1960.
|
| Series: | NASA technical report ;
R-76. |
| Subjects: |
MARC
| LEADER | 00000cam a2200000Ma 4500 | ||
|---|---|---|---|
| 001 | b11764374 | ||
| 003 | CoU | ||
| 005 | 20210324045220.0 | ||
| 008 | 090729s1960 dcua b f000 0 eng d | ||
| 035 | |a (OCoLC)ocn701843599 | ||
| 035 | |a (OCoLC)701843599 | ||
| 040 | |a YUS |b eng |c YUS |d OCLCQ |d OCLCF |d OCLCO |d KLG |d OCLCQ |d GAT |d COD | ||
| 043 | |a n-us--- | ||
| 049 | |a COD9 | ||
| 086 | 0 | |a NAS 1.12:76 | |
| 086 | 0 | |a NAS 1.12:76 | |
| 100 | 1 | |a Lansing, Donald L. |0 http://id.loc.gov/authorities/names/no2008014701 |1 http://isni.org/isni/0000000054504045. | |
| 245 | 1 | 0 | |a Calculated effects of body shape on the bow-shock overpressures in the far field of bodies in supersonic flow / |c by Donald L. Lansing. |
| 260 | |a Washington, D.C. : |b National Aeronautics and Space Administration, |c 1960. | ||
| 300 | |a 14 pages : |b illustrations ; |c 26 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 NASA technical report ; |v R-76. | |
| 504 | |a Includes bibliographical references (page 14) | ||
| 520 | |a The theory developed by G.B. Whitham (Communications on Pure and Applied Mathematics, August 1952) for the supersonic flow about bodies in uniform flight in a homogeneous medium is reviewed and an integral which expresses the effect of body shape upon the flow parameters in the far field is reduced to a form which may be readily evaluated for arbitrary body shapes. This expression is then used to investigate the effect of nose angle, fineness ratio, and location of maximum body cross section upon the far-field pressure jump across the bow shock of slender bodies. Curves are presented showing the variation of the shock strength with each of these parameters. It is found that, for a wide variety of shapes having equal fineness ratios, the integral has nearly a constant value. Hence, to a first order, the pressure jump in the far field is independent of the shape and depends only upon the fineness ratio. | ||
| 650 | 0 | |a Aerodynamics, Supersonic |x Research |z United States. | |
| 650 | 0 | |a Shock waves |x Research |z United States. | |
| 650 | 7 | |a Aerodynamics, Supersonic |x Research. |2 fast |0 (OCoLC)fst00798228. | |
| 650 | 7 | |a Shock waves |x Research. |2 fast |0 (OCoLC)fst01116740. | |
| 651 | 7 | |a United States. |2 fast |0 (OCoLC)fst01204155. | |
| 710 | 2 | |a Langley Research Center. |0 http://id.loc.gov/authorities/names/n79134855 |1 http://isni.org/isni/0000000406376754. | |
| 710 | 1 | |a United States. |b National Aeronautics and Space Administration. |0 http://id.loc.gov/authorities/names/n78087581 |1 http://isni.org/isni/0000000449071619. | |
| 830 | 0 | |a NASA technical report ; |v R-76. |0 http://id.loc.gov/authorities/names/n86725082. | |
| 907 | |a .b117643749 |b 04-01-21 |c 03-24-21 | ||
| 998 | |a gov |b 03-24-21 |c a |d m |e - |f eng |g dcu |h 0 |i 1 | ||
| 907 | |a .b117643749 |b 03-24-21 |c 03-24-21 | ||
| 944 | |a MARS - RDA ENRICHED | ||
| 946 | |a yh | ||
| 999 | f | f | |i ba77830b-1a77-5e63-a3e6-cf5ace0f229e |s a9876917-e96b-5521-9ec8-6af501535d61 |
| 952 | f | f | |p Can circulate |a University of Colorado Boulder |b Boulder Campus |c Norlin |d Norlin Library - Government Information - US |e NAS 1.12:76 |h Superintendent of Documents classification |i document |m U183075211260 |n 1 |