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. |
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great book of method of compressible flow measurement.........
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great book for PG students
Contents
DEFINITIONS AND BASIC RELATIONS | 3 |
4 | 28 |
THE ENERGY EQUATION | 45 |
RATE EQUATIONS FOR A CONTROL VOLUME | 73 |
the RankineHugoniot equations | 184 |
FLOW WITH OBLIQUE SHOCK WAVES | 219 |
normal shock equations | 236 |
FLOW IN CONSTANT AREA DUCTS | 265 |
AIRCRAFT PROPULSION | 453 |
ROCKET PROPULSION | 503 |
MISCELLANEOUS PROBLEMS | 587 |
190 | 598 |
192 | 621 |
Appendices | 645 |
198 | 654 |
677 | |
Common terms and phrases
adiabatic aircraft altitude angle chamber combustion compared compression compressor constant curve decreases defined density derived Determine devices diameter diffuser direction downstream duct efficiency employed energy engine enthalpy entropy entry Equation Example exhaust exit expression Fanno flight flow rate fluid force friction fuel function gases given gives heat higher increases initial isentropic liquid lower Mach number mass flow maximum measuring normal shock nozzle oblique shock obtained parameters pipe pressure ratio propellant properties propulsion quantities Rayleigh reference relations rocket shock wave shown in Figure shows solid Solution sound specific speed stagnation pressure static pressure steady Substituting supersonic surface tables temperature test section thrust tube tunnel turbine upstream Variation various velocity volume wall др ду дх Ро