Hanley Launches Airfoil Analysis and Reference Tool

VisualFoil NACA, version 4.1 has generators for NACA airfoils that are commonly used in airplane wings, propellers, spoilers and sail boat appendages. The software allows users to quickly generate and analyze NACA 4-Digit & 4-Digit modified airfoils, NACA 5-Digit regular and reflexed airfoils, NACA 5-Digit modified airfoils and NACA 6-Digit airfoils designated by NACA 63-XYY 64-XYY, 65-XYY, 66-XYY, 63AXYY, 64AXYY, 65AXYY. Here, X represents the design lift coefficient and YY is the thickness to chord ratio in percent.

OCALA, Florida, May 10, 2001 - Hanley Innovations, a small business specializing in aerodynamics and fluid dynamics software development for education and industry, announced today the release of VisualFoil NACA, Version 4.1 for Windows 95/98/NT/2000. The latest release is an intermediate version of Hanley Innovations' VisualFoil 4.1, Dr. Hanley's airfoil analysis and reference tool that has gained acceptance amongst engineers and educators in the USA and abroad.

VisualFoil NACA, version 4.1 has generators for NACA airfoils that are commonly used in airplane wings, propellers, spoilers and sail boat appendages. The software allows users to quickly generate and analyze NACA 4-Digit & 4-Digit modified airfoils, NACA 5-Digit regular and reflexed airfoils, NACA 5-Digit modified airfoils and NACA 6-Digit airfoils designated by NACA 63-XYY 64-XYY, 65-XYY, 66-XYY, 63AXYY, 64AXYY, 65AXYY. Here, X represents the design lift coefficient and YY is the thickness to chord ratio in percent.

VisualFoil NACA 4.1 is an essential design and reference tool for aerospace engineers who need a readily available database of NACA airfoils for wings and other aerodynamic surface designs. Automotive engineers can use VisualFoil NACA to compare performance data for automobile spoilers. It is also useful to marine design engineers who need to select and analyze cross-sectional shapes for keel, rudders and centerboards.

VisualFoil NACA 4.1 can be used to compute lift, drag and moment coefficients, center of pressure and angle for zero lift, profile drag coefficient at a specific angle of attack, estimate stall angle of attack and maximum lift. The software can generate lift and drag polar graph; plot multiple curves to compare many airfoils; generate lift versus angle of attack graphs. VisualFoil NACA can also generate an O-Grid for the NACA airfoils; adjust the grid distribution near the surface of the airfoil; export airfoils to .DXF files for use in a CAD program; export airfoil coordinates to ASCII file and plot airfoils to any dimension using your windows support printer.

The cost of VisualFoil NACA $139.00 US and may be purchased and obtained over the internet from the following url: http://secure.emetrix.com/order/product.asp?PID=892736.

More information about VisualFoil NACA and other software can be found at Dr. Hanley's www site. The URL is http://www.hanleyinnovations.com.

About Patrick Hanley

Dr. Patrick E. Hanley, is the owner and founder of Hanley Innovations, a small business specializing in aerodynamics and fluid dynamics software development for education and industry. Hanley earned his B.S. degree in aerospace engineering from Polytechnic Institute of New York (Summa Cum Laude) and his S.M. and Ph.D. degrees from the department of Aeronautics and Astronautics of Massachusetts Institute of Technology (MIT). He also completed a minor in the area of management of innovation and technology at MIT's Sloan School of Management. As owner of Hanley Innovations, Hanley has written a number of software packages including VisualFoil, WingAnalysis, ModelFoil, AirfoilBrowser, Dr. Hanley's Science Graphs, Aerodynamics in Plain English, Center of Gravity Calculator, SmockSoft and PerpeturalPaper for Smocking.

Dr. Hanley can be contacted at http://www.hanleyinnovations.com.