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NACA-TN-3527
A Second-Order Shock-Expansion Method Applicable to Bodies of Revolution near Zero Lift
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:33:51Z | |
| date available | 2017-09-04T16:33:51Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | UVNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/97285 | |
| description abstract | A second-order shock-expansion method applicable to bodies of revolution near zero lift is developed. Expressions defining the pressures on noninclined bodies are derived by the use of characteristics theory in combination with properties of the flow predicted by the generalized shock-expansion method. This result is extended to inclined bodies to obtain expressions for the normal-force and pitching-moment derivatives at zero angle of attack. The method is intended for application under conditions between the ranges of applicability of the second-order potential theory and the generalized shock-expansion method - namely, when the ratio of free-stream Mach number to nose fineness ratio is in the neighborhood of 1. | |
| language | English | |
| title | NACA-TN-3527 | num |
| title | A Second-Order Shock-Expansion Method Applicable to Bodies of Revolution near Zero Lift | en |
| type | standard | |
| page | 59 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |
