NDLI: Unsteady aerodynamics of an oscillating cascade in a compressible flow field

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Unsteady aerodynamics of an oscillating cascade in a compressible flow field

Content Provider	NASA Technical Reports Server (NTRS)
Author	Boldman, Donald R. Buffum, Daniel H. Fleeter, Sanford
Copyright Year	1987
Description	Fundamental experiments were performed in the NASA Lewis Transonic Oscillating Cascade Facility to investigate and quantify the unsteady aerodynamics of a cascade of biconvex airfoils executing torsion-mode oscillations at realistic reduced frequencies. Flush-mounted, high-response miniature pressure transducers were used to measure the unsteady airfoil surface pressures. The pressures were measured for three interblade phase angles at two inlet Mach numbers, 0.65 and 0.80, and two incidence angles, 0 and 7 deg. The time-variant pressures were analyzed by means of discrete Fourier transform techniques, and these unique data were then compared with predictions from a linearized unsteady cascade model. The experimental results indicate that the interblade phase angle had a major effect on the chordwise distributions of the airfoil surface unsteady pressure, and that reduced frequency, incidence angle, and Mach number had a somewhat less significant effect.
File Size	856610
Page Count	22
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19880003964
Archival Resource Key	ark:/13960/t2v45mh30
Language	English
Publisher Date	1987-01-01
Access Restriction	Open
Subject Keyword	Aircraft Propulsion And Power Pressure Sensors Fourier Transformation Turbine Blades Phase Shift Transonic Wind Tunnels Aerodynamics Airfoils Unsteady Flow Incidence Oscillating Flow Cascade Flow Flow Distribution Unsteady Aerodynamics Flutter Analysis Compressible Flow Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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