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| Author | : Stephen Marc Batill |
| Publisher | : |
| Total Pages | : 256 |
| Release | : 1972 |
| Genre | : |
| ISBN | : |
| Author | : |
| Publisher | : DIANE Publishing |
| Total Pages | : 42 |
| Release | : 2003 |
| Genre | : |
| ISBN | : 1428995161 |
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 42 |
| Release | : 2018-05-29 |
| Genre | : |
| ISBN | : 9781720380016 |
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 | : United States. National Aeronautics and Space Administration |
| Publisher | : |
| Total Pages | : |
| Release | : 2003* |
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| ISBN | : |
| Author | : Herbert Franklin Herndon |
| Publisher | : |
| Total Pages | : 92 |
| Release | : 1963 |
| Genre | : Aerofoils |
| ISBN | : |
| Author | : Sunetra Sarkar |
| Publisher | : LAP Lambert Academic Publishing |
| Total Pages | : 204 |
| Release | : 2010-03 |
| Genre | : |
| ISBN | : 9783838347592 |
This book analyzes the unsteady, viscous flow-field of an oscillating airfoil. This has ramifications on understanding the flapping flight of natural biological systems like fishes and invertebrates. It also helps towards a better aerodynamic design and understanding of flapping types MAVs. The flow-field simulation is performed with a grid-free Lagrangian particle based solver using vorticity particles. An examination of the unsteady aerodynamic load and the qualitative wake structures are done for airfoils undergoing pitch and plunge oscillations. The propulsive behavior is investigated at medium to high frequency ranges for different relevant parameters. These are amplitude of oscillation, mean angle of attack, and rotational axis location. Asymmetric sinusoidal motions are also examined. Dynamic stall is another important aspect of unsteady aerodynamics that airfoils and wings experience during their time dependent movement at large angles of attack. Insects use this phenomenon to increase the aerodynamic loads during their large angle flapping maneuvers. This aspect is also studied in this book.
| Author | : |
| Publisher | : |
| Total Pages | : 30 |
| Release | : 1984 |
| Genre | : |
| ISBN | : |
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 26 |
| Release | : 2018-07-05 |
| Genre | : |
| ISBN | : 9781722321383 |
Fundamental experiments are performed in the NASA Lewis Transonic Oscillating Cascade Facility to investigate the torsion mode unsteady aerodynamics of a biconvex airfoil cascade at realistic values of the reduced frequency for all interblade phase angles at a specified mean flow condition. In particular, an unsteady aerodynamic influence coefficient technique is developed and utilized in which only one airfoil in the cascade is oscillated at a time and the resulting airfoil surface unsteady pressure distribution measured on one dynamically instrumented airfoil. The unsteady aerodynamics of an equivalent cascade with all airfoils oscillating at a specified interblade phase angle are then determined through a vector summation of these data. These influence coefficient determined oscillation cascade data are correlated with data obtained in this cascade with all airfoils oscillating at several interblade phase angle values. The influence coefficients are then utilized to determine the unsteady aerodynamics of the cascade for all interblade phase angles, with these unique data subsequently correlated with predictions from a linearized unsteady cascade model. Buffum, Daniel H. and Fleeter, Sanford Glenn Research Center RTOP 535-03-01...
| Author | : C. M. Wang |
| Publisher | : |
| Total Pages | : 11 |
| Release | : 1985 |
| Genre | : |
| ISBN | : |
A solution procedure is presented for the computation of dynamic stall phenomena encountered by arbitrary shaped airfoils under arbitrary flow conditions. This procedure solves the unsteady, incompressible Navier-Stokes and the unsteady boundary layer equations using an efficient, zonal approach. A number of results for a modified NACA 0012 airfoil experiencing dynamic stall are presented and compared with available numerical data. Qualitative comparisons with flow visualization experiments are also presented. (Author).
| Author | : Ismail H. Tuncer |
| Publisher | : |
| Total Pages | : 412 |
| Release | : 1988 |
| Genre | : Aerofoils |
| ISBN | : |
