Effects Of Thickness On The Aerodynamic Characteristics Of An Initial Low Speed Family Of Airfoils For General Aviation Applications
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NASA Technical Paper
Author | : United States. National Aeronautics and Space Administration |
Publisher | : |
Total Pages | : 802 |
Release | : 1978 |
Genre | : Aeronautics |
ISBN | : |
Applied Computational Aerodynamics
Author | : Russell M. Cummings |
Publisher | : Cambridge University Press |
Total Pages | : 893 |
Release | : 2015-04-27 |
Genre | : Technology & Engineering |
ISBN | : 1316240290 |
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.
Low-speed Aerodynamic Characteristics of a 17-percent-thick Medium Speed Airfoil Designed for General Aviation Applications
Author | : Robert J. McGhee |
Publisher | : |
Total Pages | : 92 |
Release | : 1980 |
Genre | : Aerodynamics |
ISBN | : |
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.
Scientific and Technical Aerospace Reports
Author | : |
Publisher | : |
Total Pages | : 1460 |
Release | : 1991 |
Genre | : Aeronautics |
ISBN | : |
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.