Hypersonic Inlet Oblique Shock Interaction with a Laminar Boundary Layer

Articles in the same Issue

1. CONTENTS
2. Use of Holography in Vibration and Flutter Study of Fans
3. Linear State Variable Dynamic Model and Estimator Design for Allison T406 Gas Turbine Engine
4. Life Enhancement of a Gas Turbine Engine by Temperature Control
5. Turbomachinery Alloys Affected by Solid Particles
6. Analysis and Matching of Gas Turbine Components
7. Theoretical Investigation of the Interaction Between a Compressor and the Components During Surge
8. Correlations for Prediction of Discharge Rate, Core Angle and Air Core Diameter of Swirl Spray Atomizers
9. LDA Measurement of the Passage Flow Field in an Annular Airfoil Cascade
10. Numerical Solution to Transonic Potential Equations on S2 Stream Surface in a Turbomachine
11. A Unified Method for Solving Aerodynamic Cascade Design Problems on an Arbitrary Surface of Revolution
12. Semi-Constant Volume Pulse Combustion for Gas Turbine Engine Starting
13. Experiment on the Effects of Vortex Generators upon the Flat Plate Boundary Layers
14. A Review of Friction Damping of Turbine Blade Vibration
15. Hypersonic Inlet Oblique Shock Interaction with a Laminar Boundary Layer
16. Cathode and Insulator Materials for a 30 kW Arcjet Thruster
17. Improving the Development Process for Main Combustor Exit Temperature Distribution