Fundamentals of Compressible Flow: SI Units with Aircraft and Rocket PropulsionThe Subject Of Compressible Flow Or Gas Dynamics Deals With The Thermo-Fluid Dynamic Problems Of Gases And Vapours. It Is Now An Important Part Of The Undergraduate And Postgraduate Curricula. Fundamentals Of Compressible Flow Covers This Subject In Fourteen Well Organised Chapters In A Lucid Style. A Large Mass Of Theoretical Material And Equations Has Been Supported By A Number Of Figures And Graphical Depictions. Author'S Sprawling Teaching Experience In This Subject And Allied Areas Is Reflected In The Clarity, And Systematic And Logical Presentation. Salient Features * Begins With Basic Definitions And Formulas. * Separate Chapters On Adiabatic Flow, Isentropic Flow And Rate Equations. * Li>Includes Basics Of The Atmosphere, And Measuring Techniques.Separate Sections On Wind Tunnels, Laser Techniques, Hot Wires And Flow Measurement. * Discusses Applications In Aircraft And Rocket Propulsion, Space Flights, And Pumping Of Natural Gas. * Contains Large Number Of Solved And Unsolved Problems.The Present Edition Has An Additional Chapter (14) On Miscellaneous Problems In Compressible Flow (Gas Dynamics). This Is Designed To Support The Tutorials, Practice Exercises And Examinations. Problems Have Been Specially Chosen For Students And Engineers In The Areas Of Aerospace, Chemical, Gas And Mechanical Engineering. |
Contents
DEFINITIONS AND BASIC RELATIONS | 3 |
1 | 18 |
43 | 24 |
49 | 30 |
THE ENERGY EQUATION | 45 |
5 | 51 |
10 | 59 |
Continuity equation conservation of mass | 73 |
FLOW WITH OBLIQUE SHOCK WAVES | 219 |
FLOW IN CONSTANT AREA DUCTS | 265 |
FLOW IN CONSTANT AREA DUCTS WITH | 309 |
MULTIDIMENSIONAL FLOW | 337 |
METHODS OF MEASUREMENT | 380 |
AIRCRAFT PROPULSION | 453 |
ROCKET PROPULSION | 503 |
MISCELLANEOUS PROBLEMS | 587 |
ISENTROPIC FLOW WITH VARIABLE AREA | 87 |
WAVE MOTION | 129 |
FLOW WITH NORMAL SHOCK WAVES | 169 |
Appendices | 645 |
Bibliography | 677 |
Common terms and phrases
a₁ adiabatic aircraft altitude angle area ratio c₁ cm² coefficient combustion chamber compressible flow compressor constant control volume cross-section density diameter diffuser downstream duct efficiency energy equation enthalpy entropy entry Example Fanno flow flow parameters friction gas tables gases given gives heat transfer incompressible inlet isentropic flow kg/m³ kg/s kJ/kg liquid propellant Lmax M₁ Mach number Mach waves mass flow rate maximum mbar normal shock oblique shock P₁ pressure and temperature pressure ratio propellant grain propellant rockets propulsion Rayleigh line rocket engine shock wave shown in Figure sin² solid propellant specific impulse stagnation pressure stagnation temperature static pressure subsonic Substituting from Equation supersonic flow T₁ T₂ test section throat tube tunnel turbine upstream Variation velocity of sound YM² Ρι др ду дх Ро