Wind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)-0317) designed for general aviation applications. The results were compared with data for the 17 percent thick low speed airfoil (LS(1)-0417) and the 13 percent thick medium speed airfoil (MS(1)-0313). Theoretical predictions of the drag rise characteristics of this airfoil are also provided. The tests were conducted in the Langley low turbulence pressure tunnel over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2 million to 12 million, and an angle of attack range from about -8 to 20 deg.

This computational aerodynamics textbook is written at the undergraduate level, based on years of teaching focused on developing the engineering skills required to become an intelligent user of aerodynamic codes. This is done by taking advantage of CA codes that are now available and doing projects to learn the basic numerical and aerodynamic concepts required. This book includes a number of unique features to make studying computational aerodynamics more enjoyable. These include: • The computer programs used in the book's projects are all open source and accessible to students and practicing engineers alike on the book's website, www.cambridge.org/aerodynamics. The site includes access to images, movies, programs, and more • The computational aerodynamics concepts are given relevance by CA Concept Boxes integrated into the chapters to provide realistic asides to the concepts • Readers can see fluids in motion with the Flow Visualization Boxes carefully integrated into the text.

Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

"An investigation was conducted in the Langley low-turbulence pressure tunnel to determine the low-speed two-dimensional aerodynamic characteristics of a 17-percent thick airfoil designed for general aviation applications. The results are compared with a typical older NACA 65 series airfoil section. Also, a comparison between experimental data and predictions, based on a theoretical method for calculating the viscous flow about the airfoil, is presented. The tests were conducted over a Mach number range from 0.10 to 0.28 and an angle-of-attack range from -10° to 24°. Reynolds numbers, based on the airfoil chord, were varied from about 2.0x106 to 20.0x106. The results of the investigation indicate that maximum section lift coefficients increased rapidly at Reynolds numbers from about 2.0x106 to 6.0x106 and attained values greater than 2.0 for the plain airfoil and greater than 3.0 with a 20-percent-chord split flap deflected 60°. Stall characteristics were generally gradual and of the trailing-edge type either with or without the split flap. At a lift coefficient of 1.0 (climb condition) the section lift-drag ratio increased from about 65 to 85 as the Reynolds number increased from about 2.0x106 to 6.0x106. Maximum section lift coefficients were about 30 percent greater than that of a typical older NACA 65 series airfoil section and the section lift-drag ratio at a lift coefficient of 0.90 was about 50 percent greater. Agreement of experimental results with predictions based on a theoretical method which included viscous effects was good for the pressure distributions as long as no boundary-layer flow separation was present, but the theoretical method predicted drag values greatly in excess of the measured values."--Page 1