An Experimental And Computational Investigation Of Oscillating Airfoil Unsteady Aerodynamics At Large Mean Incidence Nasa Cr 2003 212199 PDF Download
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Author | : |
Publisher | : DIANE Publishing |
Total Pages | : 42 |
Release | : 2003 |
Genre | : |
ISBN | : 1428995161 |
Download An Experimental and Computational Investigation of Oscillating Airfoil Unsteady Aerodynamics at Large Mean Incidence Book in PDF, ePub and Kindle
Author | : United States. National Aeronautics and Space Administration |
Publisher | : |
Total Pages | : |
Release | : 2003* |
Genre | : |
ISBN | : |
Download An Experimental and Computational Investigation of Oscillating Airfoil Unsteady Aerodynamics at Large Mean Incidence ... Nasa/cr--2003-212199 Book in PDF, ePub and Kindle
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 42 |
Release | : 2018-05-29 |
Genre | : |
ISBN | : 9781720380016 |
Download An Experimental and Computational Investigation of Oscillating Airfoil Unsteady Aerodynamics at Large Mean Incidence Book in PDF, ePub and Kindle
A major challenge in the design and development of turbomachine airfoils for gas turbine engines is high cycle fatigue failures due to flutter and aerodynamically induced forced vibrations. In order to predict the aeroelastic response of gas turbine airfoils early in the design phase, accurate unsteady aerodynamic models are required. However, accurate predictions of flutter and forced vibration stress at all operating conditions have remained elusive. The overall objectives of this research program are to develop a transition model suitable for unsteady separated flow and quantify the effects of transition on airfoil steady and unsteady aerodynamics for attached and separated flow using this model. Furthermore, the capability of current state-of-the-art unsteady aerodynamic models to predict the oscillating airfoil response of compressor airfoils over a range of realistic reduced frequencies, Mach numbers, and loading levels will be evaluated through correlation with benchmark data. This comprehensive evaluation will assess the assumptions used in unsteady aerodynamic models. The results of this evaluation can be used to direct improvement of current models and the development of future models. The transition modeling effort will also make strides in improving predictions of steady flow performance of fan and compressor blades at off-design conditions. This report summarizes the progress and results obtained in the first year of this program. These include: installation and verification of the operation of the parallel version of TURBO; the grid generation and initiation of steady flow simulations of the NASA/Pratt&Whitney airfoil at a Mach number of 0.5 and chordal incidence angles of 0 and 10 deg.; and the investigation of the prediction of laminar separation bubbles on a NACA 0012 airfoil.Capece, Vincent R. and Platzer, Max F.Glenn Research CenterUNSTEADY AERODYNAMICS; TURBOMACHINERY; AIRFOILS; AEROELASTICITY; GAS TURBINE ENGINES; INCIDENCE; FORCED VIBRATION
Author | : Jason Neil Hayden |
Publisher | : |
Total Pages | : 98 |
Release | : 2003 |
Genre | : |
ISBN | : |
Download Unsteady Aerodynamics of an Airfoil Cascade at Large Mean Incidence Due to a Single Airfoil Oscillating in a Pitching Motion Book in PDF, ePub and Kindle
Author | : Stephen Marc Batill |
Publisher | : |
Total Pages | : 256 |
Release | : 1972 |
Genre | : |
ISBN | : |
Download An Investigation of Unsteady Aerodynamics on an Oscillating Airfoil Book in PDF, ePub and Kindle
Author | : Daniel H. Buffman |
Publisher | : |
Total Pages | : 18 |
Release | : 1996 |
Genre | : |
ISBN | : |
Download Oscillating Cascade Aerodynamics at Large Mean Incidence Book in PDF, ePub and Kindle
Presented at the International Gas Turbine and Aeroengine Congress & Exhibition Birmingham, UK - June 10-13, 1996.
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 64 |
Release | : 2018-05-29 |
Genre | : |
ISBN | : 9781720448167 |
Download Comparison of Theoretical and Experimental Unsteady Aerodynamics of Linear Oscillating Cascade with Supersonic Leading-Edge Locus Book in PDF, ePub and Kindle
An experimental influence coefficient technique was used to obtain unsteady aerodynamic influence coefficients and, consequently, unsteady pressures for a cascade of symmetric airfoils oscillating in pitch about mid-chord. Stagger angles of 0 deg and 10 deg were investigated for a cascade with a gap-to-chord ratio of 0.417 operating at an axial Mach number of 1.9, resulting in a supersonic leading-edge locus. Reduced frequencies ranged from 0.056 to 0.2. The influence coefficients obtained determine the unsteady pressures for any interblade phase angle. The unsteady pressures were compared with those predicted by several algorithms for interblade phase angles of 0 deg and 180 deg.Ramsey, John K. and Erwin, DanGlenn Research CenterUNSTEADY AERODYNAMICS; INFLUENCE COEFFICIENT; PRESSURE MEASUREMENT; PRESSURE OSCILLATIONS; WIND TUNNEL TESTS; CASCADE FLOW; MACH NUMBER; SUPERSONIC FLUTTER; AIRFOIL OSCILLATIONS; PRESSURE DISTRIBUTION; SUPERSONIC WIND TUNNELS
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Total Pages | : 16 |
Release | : 1980 |
Genre | : |
ISBN | : |
Download Experimental Studies of Scale Effects on Oscillating Airfoils at Transonic Speeds Book in PDF, ePub and Kindle
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 228 |
Release | : 2018-06-27 |
Genre | : |
ISBN | : 9781721940967 |
Download An Experimental Investigation of Unsteady Surface Pressure on an Airfoil in Turbulence Book in PDF, ePub and Kindle
Measurements of fluctuating surface pressure were made on a NACA 0015 airfoil immersed in grid generated turbulence. The airfoil model has a 2 ft chord and spans the 6 ft Virginia Tech Stability Wind Tunnel test section. Two grids were used to investigate the effects of turbulence length scale on the surface pressure response. A large grid which produced turbulence with an integral scale 13% of the chord and a smaller grid which produced turbulence with an integral scale 1.3% of the chord. Measurements were performed at angles of attack, alpha from 0 to 20 . An array of microphones mounted subsurface was used to measure the unsteady surface pressure. The goal of this measurement was to characterize the effects of angle of attack on the inviscid response. Lift spectra calculated from pressure measurements at each angle of attack revealed two distinct interaction regions; for omega(sub r) = omega b / U(sub infinity) is less than 10 a reduction in unsteady lift of up to 7 decibels (dB) occurs while an increase occurs for omega(sub r) is greater than 10 as the angle of attack is increased. The reduction in unsteady lift at low omega(sub r) with increasing angle of attack is a result that has never before been shown either experimentally or theoretically. The source of the reduction in lift spectral level appears to be closely related to the distortion of inflow turbulence based on analysis of surface pressure spanwise correlation length scales. Furthermore, while the distortion of the inflow appears to be critical in this experiment, this effect does not seem to be significant in larger integral scale (relative to the chord) flows based on the previous experimental work of McKeough suggesting the airfoils size relative to the inflow integral scale is critical in defining how the airfoil will respond under variation of angle of attack. A prediction scheme is developed that correctly accounts for the effects of distortion when the inflow integral scale is small relative t
Author | : |
Publisher | : |
Total Pages | : 684 |
Release | : 1989 |
Genre | : Aerodynamics, Transonic |
ISBN | : |
Download Transonic Unsteady Aerodynamics and Aeroelasticity, 1987 Book in PDF, ePub and Kindle