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Journal of Propulsion Technology
1001-4055
2014 Issue 5
Research of Explicit Algebraic Reynolds Stress Model in Supersonic/Hypersonic Flow Field Computation
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page:577-583
An Improved One-Dimensional Analysis Model for Ramjet
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page:584-590
Experimental Research on Performance of High Subsonic Aspirated Cascade
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page:591-596
Improving the Performance of Turbine Based on a New Optimization Design Method
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page:597-602
Conjugate Heat Transfer Optimization for Blade Profiles and Cooling Structure in Turbine Rotor
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page:603-609
Study on Negative Effects on Rotational Speeds Difference Caused by Turbine Fan Engine Gas Path Components Performance Deteriorations
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page:610-617
Numerical Investigations on Heat Transfer Characteristics of Turbine Blade with Squealer Tip
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page:618-623
Design Method of Endwall Profiling Based on Bezier Curves
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page:624-631
Numerical Study on Flow Structure and Loss of Large Expansion Ratio Transonic Turbine
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page:632-640
Effects of Total Pressure Distortion on Stator End-Wall Flow Structure of a Transonic Compressor
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page:641-647
Study on Emission Spectroscopy and Flame of Boron Combustion in Different Atmosphere
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page:648-653
Large Eddy Simulation of CH4/Air Lifted Flame
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page:654-660
Effects of Partly Covered Shape on an Isothermal and Exothermic Cavity Flowfield
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page:661-667
Effects of Diameter Ratio of Holes and Impingement Distance on Cooling Performance of Impingement/Effusion Cooled Heat Shield
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page:668-674
Effects of Hardware Geometry of Dual-Stage Swirl Cup on Ignition Performance
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page:675-680
Method for Fatigue Life Prediction of Notched Specimen with Considered Stress Relaxation
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page:681-687
Wavelet Analysis of Direct Absorption Spectroscopy
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page:688-693
Preparation, Characterization, and Effects on Thermal Decomposition of ADN of Nano Al/GAP Composite Particles
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page:694-700
Numerical Study on Pressure Loss for Gel Propellants Supply Pipeline
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page:701-707
Research on Numerical Simulation Method of Grain Strength Based on Damage Constitutive Model under High Overload
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page:708-713
Numerical Analysis of Flowfield in a Duct Embedded Rockets
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page:714-720