Author: Kasim BiberPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 480
Book Description
Experimental Studies of a Two-element Airfoil with Large Separation
Author: Kasim BiberPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 480
Book Description
Experimental Studies of a Two-element Airfoil
Author: Experimental Study of Lift-enhancing Tabs on a Two-element Airfoil
Author: Bruce L. StormsPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 7
Book Description
Experimental and Computational Investigation of Lift-Enhancing Tabs on a Multi-Element Airfoil
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781723047541
Category :
Languages : en
Pages : 158
Book Description
An experimental and computational investigation of the effect of lift-enhancing tabs on a two-element airfoil has been conducted. The objective of the study was to develop an understanding of the flow physics associated with lift-enhancing tabs on a multi-element airfoil. An NACA 63(2)-215 ModB airfoil with a 30% chord fowler flap was tested in the NASA Ames 7- by 10-Foot Wind Tunnel. Lift-enhancing tabs of various heights were tested on both the main element and the flap for a variety of flap riggings. A combination of tabs located at the main element and flap trailing edges increased the airfoil lift coefficient by 11% relative to the highest lift coefficient achieved by any baseline configuration at an angle of attack of 0 deg, and C(sub 1max) was increased by 3%. Computations of the flow over the two-element airfoil were performed using the two-dimensional incompressible Navier-Stokes code INS2D-UP. The computed results predicted all of the trends observed in the experimental data quite well. In addition, a simple analytic model based on potential flow was developed to provide a more detailed understanding of how lift-enhancing tabs work. The tabs were modeled by a point vortex at the air-foil or flap trailing edge. Sensitivity relationships were derived which provide a mathematical basis for explaining the effects of lift-enhancing tabs on a multi-element airfoil. Results of the modeling effort indicate that the dominant effects of the tabs on the pressure distribution of each element of the airfoil can be captured with a potential flow model for cases with no flow separation. Ashby, Dale L. Ames Research Center LIFT; AIRFOILS; TABS (CONTROL SURFACES); WIND TUNNEL TESTS; ANGLE OF ATTACK; NAVIER-STOKES EQUATION; COMPUTATIONAL FLUID DYNAMICS; GRID GENERATION (MATHEMATICS); AIRFOIL PROFILES; FLAPS (CONTROL SURFACES); TRAILING EDGES; INCOMPRESSIBLE FLOW; DATA CORRELATION; PREDICTION ANALYSIS TECHNIQUES; VORTICES; POTENTIAL FLOW; PRESSURE DISTRIBUTION; AERODYNAMIC C...
Theoretical and Experimental Studies of Airfoil Characteristics in Nonuniform Sheared Flow
Author: William Gordon BradyPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 110
Book Description
Work is reported on a continuation of the experimental study of the two-dimensional wing in a three-dimensional sheared flow and also treats the theory of two-dimensional nonuniform sheared flows in an attempt to determine the mechanism responsible for the marked changes in airfoil stall characteristics which were demonstrated experimentally in Reference 3. It was felt desirable to complete the three-dimensional experimental program before resuming experimental work with two-dimensional nonuniform sheared flows. The experimental wing data obtained are presented and compared, where possible, with relevant two-dimensional data and with theory.
Correlation of Theoretical and Experimental Studies of Airfoil Characteristics with Changing Angle of Attack as Affected by Time Between Changes
Author: Gordon Haakon StromPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 636
Book Description
Scientific and Technical Aerospace Reports
Author: Development of Theoretical Method for Two-Dimensional Multi-Element Airfoil Analysis and Design. Part I: Viscous-Flow Analysis Method
Author: Ishwar C. BhateleyPublisher:
ISBN:
Category :
Languages : en
Pages : 379
Book Description
A method has been developed for the analysis of arbitrary multi-element airfoils in viscous flow. The viscous solution is obtained through an inviscid analysis of an equivalent system defined from viscous considerations. An iterative procedure has been formulated to implement this analysis. The inviscid solution is obtained through a distributed singularity method. A finite-difference method is used to determine boundary-layer characteristics. Methods are included to predict laminar-flow bubbles and separation and transition points. The equivalent airfoil is defined for airfoils with attached flow as well as for airfoils with flow separation. The validity of the method is established through comparison of the predicted results with experimental data for several single- and multi-element airfoils. The comparisons show good agreement for lift coefficient and maximum lift coefficient and fair agreement for drag and pitching moment coefficients. Details of the computer program developed to implement this method are described, including input and output details, FORTRAN source deck listing, and a sample problem. (Author).
Author: H. C. Seetharam
Author: Thomas J. Mueller