An airfoil is a cross-sectional shape used on wings and other streamlined surfaces. The questions answered below discuss the different types of airfoils, how they are designed and analyzed, and their various applications.
I need to know the lift and drag of a symmetric airfoil as a function of
the angle of attack from 0 degrees to 90 degrees. I have seen tables for
Please send me information on the NACA 4, 5 and 6 digit airfoils. I would like to know some general information, their applications, advantages, disadvantages, and the formulas used to calculate the coordinates. What are the mathematical definitions of NACA profiles such as 0003.46-64.069...I've found 4- and 5-digit NACA airfoil generators, but they don't seem to do the job. Can you provide any help?
I am interested in defining the airfoils for the A-4 Skyhawk and S-3 Viking. The section designations are of the form NACA 0008-1.1-25 and 0016.3-1.03 32.7/1.00. I have read your previous explanations on modified four and five digit aifoils and still have a hard time defining it. Can you help me out?
I am doing my utmost to build a 100% scale radio-controlled flying model of the FB-111A. The airfoil sections listed for this aircraft are the NACA 64A210.68 and 64A209.80. Can you explain what these names mean and how to compute the airfoil coordinates?
I found experimental data for the NACA 0012 airfoil at a Reynolds number of 179,000. According to this data, stall occurred at an angle of attack of 10° and the lift coefficient at this angle was 0.7065. ... Can you provide a plot of lift coefficient versus alpha for this airfoil at that Reynolds number?
I want to know about the airfoil sections 622 and 625 and the equations used to calculate these three-digit configurations. Do you have references about these airfoil sections? How do you construct their shapes? Do you also have graphs showing the lift and drag versus angle of attack for these shapes?
I'm learning how to use a CFD program and I would like to test a supercritical airfoil to compare with classic airfoils. The problem is that I can't find the coordinates of a supercritical shape. Could you please help me?
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