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Aerospace propulsion / / T.-W. Lee
| Aerospace propulsion / / T.-W. Lee |
| Autore | Lee T.-W (Tae-Woo) |
| Pubbl/distr/stampa | Chichester, England : , : Wiley, , 2014 |
| Descrizione fisica | 1 online resource (318 p.) |
| Disciplina | 629.1/1 |
| Collana | Aerospace Series |
| Soggetto topico |
Airplanes - Jet propulsion
Rocketry |
| Soggetto genere / forma | Electronic books. |
| ISBN |
1-118-53469-7
1-118-53465-4 |
| Formato | Materiale a stampa  |
| Livello bibliografico | Monografia |
| Lingua di pubblicazione | eng |
| Nota di contenuto | Principle of thrust -- Basic analyses of gas-turbine engines -- Gas-turbine components : inlets and nozzles -- Compressors and turbines -- Combustors and afterburners -- Gas-turbine analysis with efficiency terms -- Basics of rocket propulsion -- Rocket propulsion and mission analysis -- Chemical rockets -- Non-chemical rockets. |
| Record Nr. | UNINA-9910453680003321 |
Lee T.-W (Tae-Woo)
|
||
| Chichester, England : , : Wiley, , 2014 | ||
| Materiale a stampa | ||
| Lo trovi qui: Univ. Federico II | ||
| ||
Aerospace propulsion / / T.-W. Lee
| Aerospace propulsion / / T.-W. Lee |
| Autore | Lee T.-W (Tae-Woo) |
| Pubbl/distr/stampa | Chichester, England : , : Wiley, , 2014 |
| Descrizione fisica | 1 online resource (318 p.) |
| Disciplina | 629.1/1 |
| Collana | Aerospace Series |
| Soggetto topico |
Airplanes - Jet propulsion
Rocketry |
| ISBN |
1-118-53487-5
1-118-53469-7 1-118-53465-4 |
| Formato | Materiale a stampa |
| Livello bibliografico | Monografia |
| Lingua di pubblicazione | eng |
| Nota di contenuto | Principle of thrust -- Basic analyses of gas-turbine engines -- Gas-turbine components : inlets and nozzles -- Compressors and turbines -- Combustors and afterburners -- Gas-turbine analysis with efficiency terms -- Basics of rocket propulsion -- Rocket propulsion and mission analysis -- Chemical rockets -- Non-chemical rockets. |
| Record Nr. | UNINA-9910790881803321 |
|
Lee T.-W (Tae-Woo)
|
||
| Chichester, England : , : Wiley, , 2014 | ||
| Materiale a stampa | ||
| Lo trovi qui: Univ. Federico II | ||
| ||
Aerospace propulsion / / T.-W. Lee
| Aerospace propulsion / / T.-W. Lee |
| Autore | Lee T.-W (Tae-Woo) |
| Pubbl/distr/stampa | Chichester, England : , : Wiley, , 2014 |
| Descrizione fisica | 1 online resource (318 p.) |
| Disciplina | 629.1/1 |
| Collana | Aerospace Series |
| Soggetto topico |
Airplanes - Jet propulsion
Rocketry |
| ISBN |
1-118-53487-5
1-118-53469-7 1-118-53465-4 |
| Formato | Materiale a stampa |
| Livello bibliografico | Monografia |
| Lingua di pubblicazione | eng |
| Nota di contenuto | Principle of thrust -- Basic analyses of gas-turbine engines -- Gas-turbine components : inlets and nozzles -- Compressors and turbines -- Combustors and afterburners -- Gas-turbine analysis with efficiency terms -- Basics of rocket propulsion -- Rocket propulsion and mission analysis -- Chemical rockets -- Non-chemical rockets. |
| Record Nr. | UNINA-9910812474303321 |
|
Lee T.-W (Tae-Woo)
|
||
| Chichester, England : , : Wiley, , 2014 | ||
| Materiale a stampa | ||
| Lo trovi qui: Univ. Federico II | ||
| ||
Theory of aerospace propulsion [[electronic resource] /] / Pasquale M. Sforza
| Theory of aerospace propulsion [[electronic resource] /] / Pasquale M. Sforza |
| Autore | Sforza P. M |
| Pubbl/distr/stampa | Waltham, Mass., : Academic Press, c2012 |
| Descrizione fisica | 1 online resource (703 p.) |
| Disciplina | 629.1/1 |
| Collana | Aerospace Engineering |
| Soggetto topico | Jet propulsion |
| Soggetto genere / forma | Electronic books. |
| ISBN |
1-283-29364-1
9786613293640 0-12-384889-X |
| Formato | Materiale a stampa |
| Livello bibliografico | Monografia |
| Lingua di pubblicazione | eng |
| Nota di contenuto |
Front 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
Chapter 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 3.3 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 4.1 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 4.14 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 5.10 Afterburning for Increased Thrust |
| Record Nr. | UNINA-9910457189003321 |
|
Sforza P. M
|
||
| Waltham, Mass., : Academic Press, c2012 | ||
| Materiale a stampa | ||
| Lo trovi qui: Univ. Federico II | ||
| ||
Theory of aerospace propulsion [[electronic resource] /] / Pasquale M. Sforza
| Theory of aerospace propulsion [[electronic resource] /] / Pasquale M. Sforza |
| Autore | Sforza P. M |
| Pubbl/distr/stampa | Waltham, Mass., : Academic Press, c2012 |
| Descrizione fisica | 1 online resource (703 p.) |
| Disciplina | 629.1/1 |
| Collana | Aerospace Engineering |
| Soggetto topico | Jet propulsion |
| ISBN |
1-283-29364-1
9786613293640 0-12-384889-X |
| Formato | Materiale a stampa |
| Livello bibliografico | Monografia |
| Lingua di pubblicazione | eng |
| Nota di contenuto |
Front 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
Chapter 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 3.3 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 4.1 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 4.14 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 5.10 Afterburning for Increased Thrust |
| Record Nr. | UNINA-9910781635303321 |
|
Sforza P. M
|
||
| Waltham, Mass., : Academic Press, c2012 | ||
| Materiale a stampa | ||
| Lo trovi qui: Univ. Federico II | ||
| ||
Theory of aerospace propulsion / / Pasquale M. Sforza
| Theory of aerospace propulsion / / Pasquale M. Sforza |
| Autore | Sforza P. M |
| Edizione | [1st ed.] |
| Pubbl/distr/stampa | Waltham, Mass., : Academic Press, c2012 |
| Descrizione fisica | 1 online resource (703 p.) |
| Disciplina |
629.1/1
629.11 |
| Collana | Aerospace Engineering |
| Soggetto topico | Jet propulsion |
| ISBN |
1-283-29364-1
9786613293640 0-12-384889-X |
| Formato | Materiale a stampa |
| Livello bibliografico | Monografia |
| Lingua di pubblicazione | eng |
| Nota di contenuto |
Front 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
Chapter 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 3.3 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 4.1 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 4.14 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 5.10 Afterburning for Increased Thrust |
| Record Nr. | UNINA-9910817660603321 |
|
Sforza P. M
|
||
| Waltham, Mass., : Academic Press, c2012 | ||
| Materiale a stampa | ||
| Lo trovi qui: Univ. Federico II | ||
| ||