A computer program was developed to produce the ordinates for airfoils of any thickness, thickness distribution, or camber in the NACA 6- and 6A-series. For the 6-series and for all but the leading edge of the 6A-series, agreement between the ordinates obtained from the new program and previously published values is generally within .00005 chord. Near the leading edge of the 6A-series airfoils, differences up to .00035 chord are found. (Author)
Development of a Computer Program to Obtain Ordinates for Naca-6 and 6A-Series Airfoils
1974
103 pages
Report
No indication
English