InI wrote an entirely new program based on all of the previous work that incorporated many suggestions from users of the original programs. I received a test release of this program from one of the authors, but I can't be sure that it is the final version for release. It was the intent of the authors that the program would be distributed on a NASA Langley software server, but this never became operational. My husband gets mad when i ask him to help me around the houseīoth of these computer programs have been included in the collection from Public Domain Aeronautical Software since the release of Version 1. These thicknesses are combined with 6-series mean lines to produce the final thick cambered airfoil. Unlike the other airfoils, these thickness distributions are not defined by algebraic equations, but use conformal mapping of a circle into an airfoil shape. These thickness families are combined with appropriate mean lines to produce the final thick cambered airfoil. These thickness families are defined by algebraic equations.
However, when performing parametric studies on effects of such variables as thickness, location of maximum thickness, leading- edge radius, location of maximum camber and others, it is not always easy to obtain the ordinates of the desired shapes rapidly and accurately. The ordinates for numerous specific airfoils of these families at a coarse set of data points were published in a series of NACA reports. Many of these airfoil shapes have been successfully used over the years as wing sections or tail sections for general aviation and military aircraft, as well as propellers and helicopter rotors.
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