A reference for engineers and students, this volume devotes more than 300 pages to theoretical and experimental considerations. It progresses from elementary materials to methods used in the design of NACA low-drag airfoils, and it presents techniques for using wing-section data to predict wing characteristics. Requires differential and integral calculus and elementary mechanics. 1949 edition.

The purpose of the book is to provide the reader with a basic understanding of airfoil geometry and how that geometry affects the aerodynamics of an airfoil and the characteristics of an airplane using that airfoil.

Depicts over 500 actual airfoil designs for light aircraft individually described pictorially, graphically, and by specifications, and with each giving: dimensions in span, chord, camber; percent of chord, lift to drag, center of pressure, drag & lift coefficients curves by angle of attack; and some historical information.

This book provides an introduction to unsteady aerodynamics with emphasis on the analysis and computation of inviscid and viscous two-dimensional flows over airfoils at low speeds. It begins with a discussion of the physics of unsteady flows and an explanation of lift and thrust generation, airfoil flutter, gust response and dynamic stall. This is followed by an exposition of the four major calculation methods in currents use, namely inviscid-panel, boundary-layer, viscous-inviscid interaction and Navier-Stokes methods. Undergraduate and graduate students, teachers, scientists and engineers concerned with aeronautical, hydronautical and mechanical engineering problems will gain understanding of the physics of unsteady low-speed flows and an ability to analyze these flows with modern computational methods.

Original publisher: Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; [Springfield, Va. : For sale by the National Technical Information Service], 1990. OCLC Number: (OCoLC)34350898 Subject: Rotors (Helicopters) -- Aerodynamics. Excerpt: ... M = 0.49 for both foils. This good agreement with the 6x28TT data experimentaslopemorecloselyat airfoils. Since the experimental angle of attack has is partly fortuitous in that the high turbulence level been corrected for wind-tunnel boundary effects, it in the 6x28TT causes the boundary-layer transition is not clear how one can determine the part of the to occur near the leading edge on both surfaces. difference due to inadequacy of the theory and the The variation of Cd, o with Mach number indicates part due to inadequacy of the correction to angle that the KGB theory underpredicts the drag level of attack. The predicted upper-surface boundary-of both airfoils at Mach numbers above about 0.65, a result indicative of a predicted wave drag that is ( X / C ) sep is layer separation point close to the exper-imental separation point at M--0.39 for both air-lower than that occurring on the wind-tunnel models. A predicted wave drag that is too low results in a foils. At M = 0.49, the predicted ( x / C ) sep occurs later than that indicated by the experiment for the predicted drag-divergence Mach number that is too RC ( 4 )-10, but it occurs sooner than that shown by high for the RC ( 4 )-10 but too low for the RC ( 5 )-10. A qualitative summary of the agreement of the the experiment for the RC ( 5 )-10. This highlights the theory relative to the experiment is given in the table uncertainty that an airfoil designer faces in selecting below: an airfoil when the primary design goal is to achieve Cl, ma x at Mach numbers of 0.4 and 0.5. Pitching moment. The pitching-moment co-Airfoil Cd M dcl / dc_ ( x / c ) _pl am. j efficients predicted by MCAR...

Original publisher: Moffett Field, Calif. : National Aeronautics and Space Administration, Ames Research Center ; Hanover, MD : Available from NASA Center for AeroSpace Information, [2000]. OCLC Number: (OCoLC)50820078 Excerpt: ... Ames tests. These predictions, along with the Ames test alternating angle of 10 deg ( Ref. 19 ). A single test point data, the reference point, and the polynomial fits from from this data set has also been used as a basis for Tables 1 and 2, are compared in Fig. 42. The calculations calculations using the ZETA code. The airfoil and slat are with the Baldwin-Lomax model severely overpredict the shown in Figure 43 along with comparisons of the moment, and the drag is also high. However, the experimental data and the calculations. For these tests the prediction using the Launder-Sharma model provides good main airfoil is the VR - 7 and it is identical to the airfoil results. In this sense, the Launder-Sharma model passes tested in the Ames wind tunnel tests. The baseline VR-7 the necessary condition that there must be a good and the main element shown in Fig. 43 are identical. The prediction of the extrema. However, an examination of slat is placed forward of the main airfoil and slightly the time behavior of the coefficients in Ref. 47 shows that below the mean chord line. the extrema occur over a very short range of time steps The baseline VR - 7 data show good agreement compared to the data and there is an associated phase shift. with the VR-7 dynamic stall function and this was In addition, the experimental case used here included two discussed previously, see Fig. 18. The data measured for shed vortices ( Ref. 10 ) and the Navier-Stokes calculations the configuration with the slat show a substantial increase indicate only a single vortex. in lift and, perhaps more important, a significantly reduced The direct calculation results shown here are quite penalty in terms of moment and drag. Two reference mixed and, in general, are not ...