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1 
Numerical calculation of plane steady transonic flows past thin lifting airfoils.Krupp, James Allan, January 1971 (has links)
Thesis (Ph.D.)University of Washington.

2 
Nonlinear normal force indicial responses for a 2D NACA 0015 airfoilIslam, Md Monirul. January 1991 (has links)
Thesis (M.S.)Ohio University, November, 1991. / Title from PDF t.p.

3 
NACA fourdigit airfoil section generation using cubic parametric curve segments and the golden section /Scarbrough, William T. January 1992 (has links)
Thesis (M.S.)Rochester Institute of Technology, 1992. / Typescript. Includes bibliographical references.

4 
Analytical and experimental investigation of Allen airfoil theoryLatta, Allen Fordyce 08 1900 (has links)
No description available.

5 
Airfoil pressure distribution tests as affected by tubulenceGeyer, Leo Alvin 05 1900 (has links)
No description available.

6 
Effects of porous tunnel walls on high lift airfoil testingLim, A. K. January 1970 (has links)
When a model is tested in a wind tunnel of either open or closed boundaries, the flow field around the model is modified, so that the results of a wind tunnel test do not exactly correspond to flight results. In order to obtain reliable wind tunnel data, wall corrections must be known accurately or eliminated. One approach to the elimination of wall corrections is the use of porous walls,
In this study, lift, drag and pitching moment about midchord were measured for two sets of twodimensional Clark Y airfoils, one set having no flap,, the other set having a 30% chord double slotted flap set at 45°. Each set consisted of four geometrically similar profiles with 9 inch, 14 inch, 19 inch and 24 inch chords. In order to simulate twodimensional flow, all airfoils were mounted vertically in the wind tunnel test section spanning the 27 inch height. The Reynolds number in all cases was maintained at 300,000o The airfoils were tested over a full range of angle of attack in the presence of different configurations of porous tunnel side walls. Longitudinally slotted side walls of open area ratios ranging from 5.5% to 29.6%, transversely slotted side walls of open area ratios ranging from 9.3% to 23.1% and perforated side walls of open area ratios ranging from 12.3% to 18.4% were tested.
Slot configurations were sought for which the CL versus ∝ data below CLMAX was most nearly independent of model size. For testing the airfoils with 30% chord double slotted flap at 45°, 18.5% longitudinally slotted side walls proved to be the best configuration while for testing the basic airfoil, 11.1% longitudinally slotted side walls proved the most satisfactory., The lift curve collapsed quite well at these two open areas for the two sets of airfoils, but the lift curve slope was about 15% lower than the expected value in each case. This anomaly remains unresolved.
Although the open area ratios found to be best in the present tests are not necessarily optimum values for all tunnels, they should provide useful guidelines for future tests with porous wall configurations. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate

7 
Multielement thin airfoil theoryWatt, George Donald January 1984 (has links)
A linearized, twodimensional, potential flow analysis of multielement airfoil configurations is attempted. Arguments are presented that suggest the accuracy of the linearized theory should be as good as or better than that of the wellknown oneelement thin airfoil theorydespite the large mean line curvature common to multielement configurations. The results obtained in this thesis tend to support this expectation.
Good success is achieved in developing a general twoelement tandem airfoil linearized theory. The effects of incidence, leading or trailing edge flap deflection, and camber on the overall and localized lifts and moments are summarized in integrals which are the tandem airfoil versions of the historical Munk integrals. Analytical solutions for the forces on tandem NACA airfoils are then obtained from these integrals. The expressions for the forces reduce, when the two airfoil elements come together, to the familiar oneelement thin airfoil theory formulas for an airfoil with a simple flap. All the forces are calculated on a small handheld computer and the results are compared with exact potential flow theory.
The overall force results for the tandem airfoil incidence problem are particularly
simple and, in fact, this simplicity allows the solution of the incidence problem for an arbitrary number of inline airfoils.
Although thickness has no effect on tandem thin airfoil theory forces, it does affect pressures. The general thickness distribution analysis for tandem airfoils, an exceedingly simple analysis involving only elementary functions, is presented. A similar type of analysis enables the design of tandem airfoil camber lines. Examples are given.
Modelling the effects of overlap of a staggered twoelement airfoil configuration
is a much more complicated analysis than that of tandem airfoil elements. Nevertheless, substantial success is achieved. This includes the development of the equivalent Munk integrals that give the overall and localized forces on airfoil elements of arbitrary chord length, arbitrarily positioned relative to one another (providing the chord lines are approximately parallel to each other and to the flow at infinitythe linearization requirement).
Although analytical solutions are obtained for the overall forces of the incidence and flap deflection problems, they are in terms of parameters which can only be obtained through a trial and error solution of the staggered parallel slit conformal mapping. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate

8 
Development of a design tool for aerodynamic shape optimization of airfoilsSecanell Gallart, Marc. 10 April 2008 (has links)
No description available.

9 
Thin/cambered/reflexed airfoil development for microair vehicles at Reynolds numbers of 60,000 to 150,000 /Reid, Michael R. January 2006 (has links)
Thesis (M.S.)Rochester Institute of Technology, 2006. / Typescript. Includes bibliographical references (leaves 134135).

10 
Optimization of blowing and suction control on NACA0012 airfoil using genetic algoirthm with diversity controlHuang, Liang. January 2004 (has links) (PDF)
Thesis (M.S.)University of Kentucky, 2004. / Title from document title page (viewed Oct. 12, 2004). Document formatted into pages; contains xii, 113 p. : ill. Includes abstract and vita. Includes bibliographical references (p. 102112).

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