FUNDAMENTALS OF COMPRESSIBLE FLUID DYNAMICSCompressible Fluid Dynamics (or Gas Dynamics) has a wide range of applications in Mechanical, Aeronautical and Chemical Engineering.It plays a significant role in the design and development of compressors, turbines, missiles, rockets and aircrafts. This comprehensive and systematically organized book gives a clear analysis of the fundamental principles of Compressible Fluid Dynamics. It discusses in rich detail such topics as isentropic, Fanno, Rayleigh, simple and generalised one-dimensional flows. Besides, it covers topics such as conservation laws for compressible flow, normal and oblique shock waves, and measurement in compressible flow. Finally, the book concludes with detailed discussions on propulsive devices. The text is amply illustrated with worked-out examples, tables and diagrams to enable the students to comprehend the subject with ease. Intended as a text for undergraduate students of Mechanical, Aeronautical and Chemical Engineering, the book would also be extremely useful for practising engineers. |
Contents
| 1 | |
| 5 | |
| 13 | |
| 14 | |
Review Questions | 36 |
ISENTROPIC FLOW 86135 | 86 |
Illustrative Examples | 168 |
Review Questions | 180 |
1637 | 279 |
Review Questions | 288 |
Illustrative Examples | 314 |
Review Questions | 320 |
FLOW THROUGH NOZZLES AND DIFFUSER | 322 |
Review Questions | 359 |
AIR BREATHING PROPULSION | 398 |
ROCKET PROPULSION | 470 |
Illustrative Examples | 206 |
Review Questions | 214 |
Illustrative Examples | 228 |
GENERALISED ONEDIMENSIONAL FLOW | 234 |
NORMAL SHOCK WAVES | 246 |
APPENDIX Al Isentropic Flow Tables for Perfect Gas y 1 4 | 527 |
APPENDIX A5 Simple Mass Addition Tables for Perfect Gas y 1 4 | 544 |
APPENDIX A8 PrandtlMeyer Flow Tables for Perfect Gas y 1 4 | 565 |
Common terms and phrases
A₁ adiabatic area ratio back pressure calculated change in entropy choked coefficient combustion chamber compressible flow compressor constant area duct continuity equation control surface control volume corresponding decrease density derived diffuser downstream driving potential enthalpy entropy exit section expansion Fanno flow Fanno line flow Mach number flow parameters friction fuel heat transfer Hence impulse function incompressible increase inlet isentropic flow isentropic tables kg/s kinetic energy M₁ Mach number mass addition mass flow rate momentum equation N/m² normal shock nozzle oblique shock obtained one-dimensional P₁ P₂ perfect gas propellant property ratios propulsion Rayleigh flow Rayleigh line rocket engine second law shock wave shown in Fig Solution sonic speed stagnation pressure stagnation pressure ratio stagnation temperature static pressure static temperature stream subsonic supersonic flow T₁ T₂ thrust turbine upstream V₁ V₂ velocity of sound YM² zero δι
Popular passages
Page 11 - ... control volume is equal to the time rate of change of momentum within the control volume plus the excess of outgoing momentum flux over incoming momentum flux.
Page 8 - ... surroundings can be restored to their initial states without producing more than an infinitesimal change in any auxiliary system. The converse of this statement can also be shown to be true: namely, if at the completion of a process both the system and its surroundings can be restored to their initial states without requiring more than an infinitesimal change in any auxiliary system, then conditions (a) and (6) listed at the beginning of this article will have been satisfied. Therefore, a reversible...