The Influence of a Rotating Leading Edge on Accelerating Starting Flow over an Airfoil
Abstract
This Study Reports an Experimental Investigation on the Influences of a Rotating Leading Edge on Vortex Developments over an Airfoil Uniformly Accelerated from Rest. to Evaluate Such Flow, a NACA 0015 Airfoil that Incorporates a Rotating Leading Edge Was Subjected to a Nearly Constant Acceleration of 2.4 M/sec2 after Start from Rest. Flow Visualization Technique of Direct Injection of Liquid Titanium Tetrachloride Was Employed to Visualize the Flow Developments over the Airfoil. the Study Demonstrates the Roli of the Leading Edge Rotation in Controlling Flow Separation and Subsequent Vortex Development for an Angle of Attack Range between 10"And 30°. the Results Suggests that the Concept of the Rotating Leading Edge May Be Utilized to Control the Characteristics of Unsteady Separated Flows over Lifting Surfaces. This Control Possibility Seems to Be Quite Effective and Could Have Significant Consequences for Future Applications in Controlling Unsteady Separated Flows.
Recommended Citation
F. Finaish and R. W. Jefferies, "The Influence of a Rotating Leading Edge on Accelerating Starting Flow over an Airfoil," 28th Aerospace Sciences Meeting, 1990, article no. AIAA 90-0583, American Institute of Aernaughtics and Astronautics, Jan 1990.
The definitive version is available at https://doi.org/10.2514/6.1990-583
Department(s)
Mechanical and Aerospace Engineering
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2023 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 1990
