LEADER 05171nam 2200637 a 450 001 9910781635303321 005 20200520144314.0 010 $a1-283-29364-1 010 $a9786613293640 010 $a0-12-384889-X 035 $a(CKB)2550000000048218 035 $a(EBL)787252 035 $a(OCoLC)759807281 035 $a(SSID)ssj0000550673 035 $a(PQKBManifestationID)12176718 035 $a(PQKBTitleCode)TC0000550673 035 $a(PQKBWorkID)10524145 035 $a(PQKB)11790202 035 $a(Au-PeEL)EBL787252 035 $a(CaPaEBR)ebr10504586 035 $a(CaONFJC)MIL329364 035 $a(MiAaPQ)EBC787252 035 $a(PPN)158612043 035 $a(EXLCZ)992550000000048218 100 $a20110628d2012 uy 0 101 0 $aeng 135 $aur|n|---||||| 181 $ctxt 182 $cc 183 $acr 200 10$aTheory of aerospace propulsion$b[electronic resource] /$fPasquale M. Sforza 210 $aWaltham, Mass. $cAcademic Press$dc2012 215 $a1 online resource (703 p.) 225 1 $aAerospace Engineering 300 $aDescription based upon print version of record. 311 $a1-85617-912-5 320 $aIncludes bibliographical references and index. 327 $aFront Cover; Theory of Aerospace Propulsion; Copyright; Contents; Preface; Chapter 1 - Idealized Flow Machines; 1.1 Conservation Equations; 1.2 Flow Machines with No Heat Addition: The Propeller; 1.3 Flow Machines with P = 0 and Q = Constant: The Turbojet, Ramjet, and Scramjet; 1.4 Flow Machines with P = 0, Q = Constant, and A0 = 0: The Rocket; 1.5 The Special Case of Combined Heat and Power: The Turbofan; 1.6 Force Field for Air-Breathing Engines; 1.7 Conditions for Maximum Thrust; 1.8 Example: Jet and Rocket Engine Performance; 1.9 Nomenclature; Reference 327 $aChapter 2 - Quasi-One-Dimensional Flow Equations2.1 Introduction; 2.2 Equation of State; 2.3 Speed of Sound; 2.4 Mach Number; 2.5 Conservation of Mass; 2.6 Conservation of Energy; 2.7 Example: Heating Values for Different Fuel-Oxidizer Combinations; 2.8 Conservation of Species; 2.9 Conservation of Momentum; 2.10 Impulse Function; 2.11 Stagnation Pressure; 2.12 Equations of Motion in Standard Form; 2.13 Example: Flow in a Duct with Friction; 2.14 Nomenclature; References; Chapter 3 - Idealized Cycle Analysis of Jet Propulsion Engines; 3.1 Introduction; 3.2 General Jet Engine Cycle 327 $a3.3 Ideal Jet Engine Cycle Analysis3.4 Ideal Turbojet in Maximum Power Take-Off; 3.5 Ideal Turbojet in High Subsonic Cruise in The Stratosphere; 3.6 Ideal Turbojet in Supersonic Cruise in The Stratosphere; 3.7 Ideal Ramjet in High Supersonic Cruise in The Stratosphere; 3.8 Ideal Turbofan in Maximum Power Take-Off; 3.9 Ideal Turbofan in High Subsonic Cruise in The Stratosphere; 3.10 Ideal Internal Turbofan in Supersonic Cruise in The Stratosphere; 3.11 Real Engine Operations; 3.12 Nomenclature; 3.13 Exercises; References; Chapter 4 - Combustion Chambers for Air-Breathing Engines 327 $a4.1 Combustion Chamber Attributes4.2 Modeling the Chemical Energy Release; 4.3 Constant Area Combustors; 4.4 Example: Constant Area Combustor; 4.5 Constant Pressure Combustors; 4.6 Fuels for Air-Breathing Engines; 4.7 Combustor Efficiency; 4.8 Combustor Configuration; 4.9 Example: Secondary Air for Cooling; 4.10 Criteria for Equilibrium in Chemical Reactions; 4.11 Calculation of Equilibrium Compositions; 4.12 Example: Homogeneous Reactions with a Direct Solution; 4.13 Example: Homogeneous Reactions with Trial-And-Error Solution 327 $a4.14 Example: Estimation of Importance of Neglected Product Species4.15 Adiabatic Flame Temperature; 4.16 Example: Adiabatic Flame Temperature for Stoichiometric H2-O2 Mixture; 4.17 Nomenclature; References; Chapter 5 - Nozzles; 5.1 Nozzle Characteristics and Simplifying Assumptions; 5.2 Flow in a Nozzle with Simple Area Change; 5.3 Mass Flow in an Isentropic Nozzle; 5.4 Nozzle Operation; 5.5 Normal Shock inside the Nozzle; 5.6 Example: Shock in Nozzle; 5.7 Two-Dimensional Considerations in Nozzle Flows; 5.8 Example: Overexpanded Nozzles; 5.9 Example: Underexpanded Nozzles 327 $a5.10 Afterburning for Increased Thrust 330 $a Readers of this book will be able to: utilize the fundamental principles of fluid mechanics and thermodynamics to analyze aircraft engines, understand the common gas turbine aircraft propulsion systems and be able to determine the applicability of each, perform system studies of aircraft engine systems for specified flight conditions, perform preliminary aerothermal design of turbomachinery components, and conceive, analyze, and optimize competing preliminary designs for conventional and unconventional missions. 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