But the price of that performance is risk (or risk reduction efforts, depending upon your preference). There are better four digit sections, the six digit sections are in a different league, and bespoke sections tailored for the application are yet another league above in performance terms. The fact that it was possible for people displaying this rather Luddite attitude aerodynamics to be successful illustrates the over-riding difficulties of manufacturing tolerance & weight control in the golden age (& indeed at the low performance end of GA today). Its widespread popularity serves to highlight the people who basically don't care about aerofoil sections beyond a certain point (the 80-20 rule, or nobody got fired for buying IBM brigade). What seems to have happened is that people who had reasonably successful legacy aeroplanes based upon Clark Y or similar sections switched to NACA 2412 because the it's basically the same thing (low risk) but with a neat numerical definition, which makes it easier to generate accurate drawings & loft the wing shape correctly. The wings are aerofoils attached to each side of the. The four digit sections really bridge the gap between the aerodynamics of wing sections being an art and a science, because they allow a somewhat rational definition & exploration of a design space, but had an experimental-rather than theoretical-starting point. A wing is an aerofoil, which has a streamlined cross-sectional shape producing a useful lift to drag ratio. In fact, the four digit sections use a thickness distribution based upon Clark Y and Göttingen 398 (1919), because they are similar & were known to work reasonably well. (Round the final answer to the nearest whole number.) Question: The NACA 2412 airfoil is flying at a velocity of. Calculate the value of the circulation around the airfoil. NACA 2412 is basically a slightly sexier version of Clark Y (1922 vintage). The NACA 2412 airfoil is flying at a velocity of 58 m/s at a standard altitude of 3 km (see Appendix D).
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