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- Some Fundamental Aspects of Compressible Flow
| Content Provider | Scilit |
|---|---|
| Author | Oosthuizen, Patrick H. Carscallen, William E. |
| Copyright Year | 2013 |
| Description | It was indicated in the previous chapters that compressibility effects become important in a gas flow when the velocity in the flow is high. An attempt will be made in this chapter to show that it is not the value of the gas velocity itself but rather the ratio of the gas velocity to the speed of sound in the gas that determines when compressibility is important. This ratio is termed the Mach number, M, i.e., M V a = = gas velocity speed of sound (3.1) where a is the speed of sound. If M < 1, the flow is said to be subsonic, whereas if M > 1, the flow is said to be super- sonic. If the Mach number is near 1 and there are regions of both subsonic and supersonic flow, the flow is said to be transonic. If the Mach number is very much greater than 1, the flow is said to be hypersonic. Hypersonic flow is normally associated with flows in which M > 5. Book Name: Introduction to Compressible Fluid Flow |
| Related Links | https://content.taylorfrancis.com/books/download?dac=C2011-0-04015-9&isbn=9780429109843&doi=10.1201/b15414-8&format=pdf |
| Ending Page | 81 |
| Page Count | 20 |
| Starting Page | 62 |
| DOI | 10.1201/b15414-8 |
| Language | English |
| Publisher | Informa UK Limited |
| Publisher Date | 2013-07-22 |
| Access Restriction | Open |
| Subject Keyword | Book Name: Introduction To Compressible Fluid Flow Aerospace Engineering Compressibility Flow Hypersonic Transonic Supersonic Attempt Gas Velocity Subsonic Made Chapter |
| Content Type | Text |
| Resource Type | Chapter |
