Research on Aeroelastic Phenomena in Airfoil Cascades. An Experimental Investigation of the Unsteady Aerodynamics of a Controlled Oscillating MCA Airfoil Cascade.
Abstract
A unique unsteady cascade experiment directed at providing fundamental aerodynamic data needed to verify or direct refinements to the basic model on unstalled supersonic torsional flutter in turbomachines is presented. In particular, the steady, quasi-static, and unsteady aerodynamics were determined for a multiple circular arc (MCA) airfoil cascade which modeled the tip section of an advanced design fan blade. The MCA cascade was harmonically oscillated in the torsional mode at a reduced frequency value of 0.14. The fundamental unsteady aerodynamic data was obtained at a Mach number equal to 1.55 over a range of interblade phase angles for two values of the cascade static pressure ratio. These unsteady results were then correlated with the predictions from state-of-the-art unsteady flat plate cascade analyses.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1976
- Accession Number
- ADA039550
Entities
People
- Ronald E. Riffel
- Sanford Fleeter
Organizations
- General Motors