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Aerodynamically forced Response of an Airfoil Including Profile and Incidence Effects
-
Hsiao-Wei D. Chiang,
Published/Copyright:
June 1, 1990
Published Online: 1990-06
©2011 by Walter de Gruyter GmbH & Co.
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Articles in the same Issue
- CONTENTS
- Analysis of Transonic Flow Through a Lightly Loaded Compressor Rotor
- Atomization Under Engine-Burner Cross-Flow Conditions
- Inter and Intra Blade Row Laser Velocimetry Studies of Gas Turbine Compressor Flows
- Characteristics of Liquid Hydrogen Fueled Supersonic Aircraft Engine
- Aerodynamically forced Response of an Airfoil Including Profile and Incidence Effects
- Theoretical and Experimental Analysis of a Compressor Cascade at Supercritical Flow Conditions
- Experimental and Theoretical Study on Liquid Atomization into a Gas Stream
- Friction Damping of Random Vibration in Gas Turbine Engine Airfoils
- Calculation of Confined Swirling Flows
- A Variation Finite Element Method for Solving the Blade-to-Blade Flow in Centrifugal Compressor's Cascades with Splitter Blades on an Arbitrary Streamsheet of Revolution and a Mathematical Treatment to the Region Behind Cascades
- Numerical Integration of the 3D Unsteady Euler Equations for Flutter Analysis of Axial Flow Compressors
- Periodicity, Superposition, and 3D Effects in Supersonic Compressor Flutter Aerodynamics
Articles in the same Issue
- CONTENTS
- Analysis of Transonic Flow Through a Lightly Loaded Compressor Rotor
- Atomization Under Engine-Burner Cross-Flow Conditions
- Inter and Intra Blade Row Laser Velocimetry Studies of Gas Turbine Compressor Flows
- Characteristics of Liquid Hydrogen Fueled Supersonic Aircraft Engine
- Aerodynamically forced Response of an Airfoil Including Profile and Incidence Effects
- Theoretical and Experimental Analysis of a Compressor Cascade at Supercritical Flow Conditions
- Experimental and Theoretical Study on Liquid Atomization into a Gas Stream
- Friction Damping of Random Vibration in Gas Turbine Engine Airfoils
- Calculation of Confined Swirling Flows
- A Variation Finite Element Method for Solving the Blade-to-Blade Flow in Centrifugal Compressor's Cascades with Splitter Blades on an Arbitrary Streamsheet of Revolution and a Mathematical Treatment to the Region Behind Cascades
- Numerical Integration of the 3D Unsteady Euler Equations for Flutter Analysis of Axial Flow Compressors
- Periodicity, Superposition, and 3D Effects in Supersonic Compressor Flutter Aerodynamics
