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Control of unsteady separated flow associated with the dynamic stall of airfoils (Document No: 19950008199)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wilder, M. C. |
| Copyright Year | 1994 |
| Description | A unique active flow-control device is proposed for the control of unsteady separated flow associated with the dynamic stall of airfoils. The device is an adaptive-geometry leading-edge which will allow controlled, dynamic modification of the leading-edge profile of an airfoil while the airfoil is executing an angle-of-attack pitch-up maneuver. A carbon-fiber composite skin has been bench tested, and a wind tunnel model is under construction. A baseline parameter study of compressible dynamic stall was performed for flow over an NACA 0012 airfoil. Parameters included Mach number, pitch rate, pitch history, and boundary layer tripping. Dynamic stall data were recorded via point-diffraction interferometry and the interferograms were analyzed with in-house developed image processing software. A new high-speed phase-locked photographic image recording system was developed for real-time documentation of dynamic stall. |
| File Size | 4656713 |
| Page Count | 84 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19950008199 |
| Archival Resource Key | ark:/13960/t2x39qc4q |
| Language | English |
| Publisher Date | 1994-07-31 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Image Processing Airfoils Unsteady Flow Boundary Layer Control Photographic Recording Wind Tunnel Tests Angle of Attack Separated Flow Active Control Aerodynamic Stalling Leading Edges Mach Number Interferometry Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
