Abstract
In this paper, flow separation of a convergent–divergent (C-D) nozzle is placed downstream of a supersonic flow delivered from Mach 2.0 nozzle is investigated. Static pressure measurements are conducted using pressure taps. The flow characteristics of straight and slanted entry C-D nozzle are investigated for various NPR of Mach 2.0 nozzle. The effect of asymmetry at inlet by providing 15°, 30°, 45° and 57° cut is analyzed. Particular attention is given to the location of the shock within the divergent section of the test nozzle. This location is examined as a function both NPR of Mach 2.0 nozzle and test nozzle inlet angle. Some of the measurements are favorably compared to previously developed theory. A Mach number ratio of 0.81 across the flow separation region was obtained.
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©2016 by De Gruyter
Articles in the same Issue
- Frontmatter
- Probabilistic Fatigue Life Prediction of Turbine Disc Considering Model Parameter Uncertainty
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Adjoint Optimization of Multistage Axial Compressor Blades with Static Pressure Constraint at Blade Row Interface
- Wall Pressure Measurements in a Convergent–Divergent Nozzle with Varying Inlet Asymmetry
- Thermoelastic Simulations Based on Discontinuous Galerkin Methods: Formulation and Application in Gas Turbines
- Re-Educating Jet-Engine-Researchers to Stay Relevant
- Analysis of a Turbine Blade Failure in a Military Turbojet Engine
- Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model
- Design and Experimentation of Simulated Combustor Model for Aircraft Afterburner Applications
- Contact Stress Analysis and Fatigue Life Prediction of a Turbine Fan Disc
- Multidisciplinary Design Optimization on Conceptual Design of Aero-engine
Articles in the same Issue
- Frontmatter
- Probabilistic Fatigue Life Prediction of Turbine Disc Considering Model Parameter Uncertainty
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Adjoint Optimization of Multistage Axial Compressor Blades with Static Pressure Constraint at Blade Row Interface
- Wall Pressure Measurements in a Convergent–Divergent Nozzle with Varying Inlet Asymmetry
- Thermoelastic Simulations Based on Discontinuous Galerkin Methods: Formulation and Application in Gas Turbines
- Re-Educating Jet-Engine-Researchers to Stay Relevant
- Analysis of a Turbine Blade Failure in a Military Turbojet Engine
- Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model
- Design and Experimentation of Simulated Combustor Model for Aircraft Afterburner Applications
- Contact Stress Analysis and Fatigue Life Prediction of a Turbine Fan Disc
- Multidisciplinary Design Optimization on Conceptual Design of Aero-engine