Figure 1: NACA 0015 Airfoil Cross-section with Pressure Taps. NACA Airfoil Charts Every NACA airfoil has two charts to present the lift, drag, and moment coefficient data for the airfoil. AN EXPERIMENTAL LOW REYNOLDS NUMBER COMPARISON OF A WORTMA" FX67-Kl70 AIRFOIL, A NACA 0012 AIRFOIL, AND A NACA 64-210 AIRFOIL IN SIMULATED HEAVY RAIN ABSTRACT Wind tunnel experiments were conducted on Wortmann FX67-Kl70, NACA 0012, and NACA 64-210 airfoils at rain rates of 1000 mm/hr and Reynolds numbers of 310,000 to compare the aerodynamic performance degradation of the airfoils … INTRODUCTIONThis experiment analyzes the NACA 0015 airfoil in a low speed wind tunnel at varying angles of attack. There are links to the original airfoil source and dat file and the details … We ran a steady-state and a transien t simulation for 0 and 10 8 AoA. The coefficient of drag is calculated which is given in Table 3. Airfoil database search (NACA 6 series) Search the 1638 airfoils available in the databases filtering by name, thickness and camber. ConclusionAnalysis of NACA 23012 and NACA 2415 airfoil … Airfoils were examined for lift and drag performance as well as surface pressure and flow field characteristics. NACA 6-Series (NLF) Airfoil Airfoils with emphasis on maximizing Natural Laminar Flow (NLF). 1 The discussion is organized according to the application (i.e., free flight model airfoils are first discussed, then F3B airfoils … The airfoil is described using six digits in the following sequence: 1. data acquisition computer. The first chart will have curves of lift coefficient versus angle of attack at various Reynolds numbers and curves of moment coefficient at the quarter chord point versus angle of attack at various Reynolds numbers. The number "6" indicating the series (NACA 6-Series NLF Airfoil). Downstream of the 2 0 0 . Symmetric airfoils are used in many applications including aircraft vertical stabilizers, submarine fins, rotary and some fixed wings. Figure 6.47 shows the evolution of z-vorticity contour (left) of the flow and upper surface skin friction coefficient (right) of the NACA 0012 airfoil predicted by the Mesh-B (fine mesh) case with Gieseking’s model during upstroke pitching, starting from angle of attack of 14.38° and continuing to 25.98°. Validating the NACA 2412 airfoil is a time-dependent proce ss, so it should be modeled with a time-dependent simulation. Since the airfoil is placed at 4° angle of attack, it generates drag. The airfoils investigated in this study include NACA 0009, NACA 0012 (conventional and reversed configuration), Clark-Y, flat plate airfoils (1, 3, and 5% thickness), and thin cambered plates (3, 6, and 9% camber). 2 0 . The NACA 4 digit and 5 digit airfoils were created by superimposing a simple meanline shape with a thickness distribution that was obtained by fitting a couple of popular airfoils of the time: +- y = (t/0.2) * (.2969*x 0.5 - .126*x - .3537*x 2 + .2843*x 3 - .1015*x 4 ) was utilized. 4 0 . The locations of these pressure taps are shown below in Figure 1. In general, it is One digit describing the distance of the minimum pressure area in tens of percent of chord. Click on an airfoil image to display a larger preview picture. The NACA 0015 is a symmetrical airfoil with a 15% thickness to chord ratio. 6 0 . 8 1 - 0 . If the airfoil is placed at some angle of attack in a moving fluid, it will create some drag. The NACA 0012 airfoil is symmetrical; the 00 indicates that it has no camber. From Summary: "The historical development of NACA airfoils is briefly reviewed. 2. In Chapter 3, a discussion of all the airfoils is given first; then the figures (airfoil plots and performance data) are presented in Chapter 4. The 12 indicates that the airfoil has a 12% thickness to chord length ratio; it is 12% as thick as it is long. This valve allows measurements to be taken of each pressure tap individually and progressively incremented one by one through the computer. number airfoil data. New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils.