Author: Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Unsteady Transonic Flow on Airfoils and in Cascades
Author: Unsteady Transonic Flow with Shocks Around Oscillating Airfoils and Cascades
Author: Liu Gao-lianA Linear Aerodynamic Analysis for Unsteady Transonic Cascades
Author: Joseph M. VerdonPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 84
Book Description
The Calculation of Steady and Unsteady Transonic Flow in Cascades
Author: D. S. WhiteheadPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 140
Book Description
Computation of unsteady transonic flows through rotating and stationary cascades
Author: John I. ErdosComputation of Unsteady Transonic Flows Through Rotating and Stationary Cascades: Method of analysis
Author: Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 142
Book Description
Perturbation Analysis of Steady and Unsteady Transonic Flow Through Cascades
Author: A. KluwickUnsteady Transonic Flow
Author: Mårten LandahlPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 152
Book Description
Unsteady Aerodynamic Response of a Linear Cascade of Airfoils in Separated Flow
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721147588
Category :
Languages : en
Pages : 108
Book Description
The overall objective of this research program was to investigate methods to modify the leading edge separation region, which could lead to an improvement in aeroelastic stability of advanced airfoil designs. The airfoil section used is representative of current low aspect ratio fan blade tip sections. The experimental potion of this study investigated separated zone boundary layer from removal through suction slots. Suction applied to a cavity in the vicinity of the separation onset point was found to be the most effective location. The computational study looked into the influence of front camber on flutter stability. To assess the influence of the change in airfoil shape on stability the work-per-cycle was evaluated for torsion mode oscillations. It was shown that the front camberline shape can be an important factor for stabilizing the predicted work-per-cycle and reducing the predicted extent of the separation zone. In addition, data analysis procedures are discussed for reducing data acquired in experiments that involve periodic unsteady data. This work was conducted in support of experiments being conducted in the NASA Glenn Research Center Transonic Flutter Cascade. The spectral block averaging method is presented. This method is shown to be able to account for variations in airfoil oscillation frequency that can occur in experiments that force oscillate the airfoils to simulate flutter. Capece, Vincent R. and Ford, Christopher and Bone, Christopher and Li, Rui Glenn Research Center NAG3-2695
Unsteady Transonic Flow Past Airfoils in Rigid Body Motion...
Author: Chang I-ChungPublisher: Hardpress Publishing
ISBN: 9781314777147
Category :
Languages : en
Pages : 210
Book Description
Unlike some other reproductions of classic texts (1) We have not used OCR(Optical Character Recognition), as this leads to bad quality books with introduced typos. (2) In books where there are images such as portraits, maps, sketches etc We have endeavoured to keep the quality of these images, so they represent accurately the original artefact. Although occasionally there may be certain imperfections with these old texts, we feel they deserve to be made available for future generations to enjoy.