The general methods used to derive the basic thickness forms for NACA 6- and 7- series airfoils and their corresponding pressure distributions are presented. Detail data necessary for the application of NACA 6-serles airfoils to wing design are presented in supplementary figures, together with recent data for the NACA 24-, 44-, and 230- series airfoils. Most of the data on airfoil section characteristics were obtained in the Langley two-dimensional low-turbulence pressure tunnel. The flight data consist largely of drag measurements made by the wake-survey method. Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar as possible. The data are presented in the form of pressure-distribution diagrams and as graphs of calculated coefficients for the airfoil-and-flap combination and for the flap alone. A test installation was used in which the airfoil was mounted horizontally in the wind tunnel between vertical end planes so that two-dimensional flow was approximated. The pressures were measured on the upper and lower surfaces at one chord section on both the main airfoil and on the flap for several different flap deflections and at several angles of attack. Report presents the results of pressure-distribution tests of an NACA 23012 airfoil with an NACA 23012 external airfoil flap made in the 7 by 10-foot wind tunnel. Pressure distribution over an NACA 23012 airfoil with an NACA 23012 external- airfoil flap
Each airfoil data bank computer code was written to be used on the Amdahl Computer system, which is IBM compatible and uses Fortran. The various component of each computer code, the source of the data used to create the airfoil data bank, the limitations of each data bank, program listing, and a sample case with its associated input-output are described. The families chosen consisted of the Clark-Y, NACA 16 series, and NACA 4 digit series airfoils. Realizing the need for such data, a study was initiated to provide airfoil data banks for three commonly used airfoil families in propeller design and analysis. Inherent in the majority of the theoretical performance models to date is the need for airfoil data banks which provide lift, drag, and moment coefficient values as a function of Mach number, angle-of-attack, maximum thickness to chord ratio, and Reynolds number. With the renewed interest in propellers as means of obtaining thrust and fuel efficiency in addition to the increased utilization of the computer, a significant amount of progress was made in the development of theoretical models to predict the performance of propeller systems. Sample calculations for an NACA 63(2)-015 airfoil showed an annual energy output increase of 17-27 percent, depending on rotor solidity, compared to an NACA 0015 airfoil.Īerodynamic data banks for Clark-Y, NACA 4-digit and NACA 16- series airfoil families Results indicated that NACA 6- series airfoils yield peak power coefficients as great as NACA 4-digit airfoils and have broader and flatter power coefficient-tip speed ratio curves. Performance estimates were made using a blade element/momentum theory approach. Ten different airfoils, having thickness-to-chord ratios of 12, 15, and 18 percent, were studied. Analysis was limited to curved-bladed machines having rotor solidities of 7-21 percent and operating at a Reynolds number of 3 x 10 to the 6th. The aerodynamic efficiency of Darrieus wind turbines as effected by blade airfoil geometry was investigated.
Comparison of NACA 6- series and 4-digit airfoils for Darrieus wind turbines