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Research on Aeroelastic Phenomena in Airfoil Cascades; Supersonic Unsteady Aerodynamic Phenomena in a Controlled Oscillating Cascade.
GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
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A unique supersonic inlet flow field unsteady cascade experiment is described wherein the time-dependent pressure distribution within a harmonically oscillating airfoil cascade is quantitatively determined. The torsional frequency of oscillation and the interblade phase angle are precisely controlled by means of on-line digital computers. The dynamic data obtained include the chordwise distribution of the unsteady pressure magnitude and its phase lag as referenced to the airfoil motion. Parameters varied include the cascade inlet Mach number, the interblade phase angle, the torsional axis location, and the reduced frequency. All of the data is correlated with state-of-the-art analytical predictions. Author
APPROVED FOR PUBLIC RELEASE