Details of airfoil (aerofoil) (n63010a-il) NACA 63A010 AIRFOIL NACA 63-010A airfoil

Max thickness 10% at 34.9% chord.

Max thickness 15% at 37.1% chord. Gottingen 765 airfoil (recovered).

SUMMARY Basic thickness forms of the NACA 63-, 6_-, 65- series and NACA 63A-, 6_A-, 65A-series airfoil sections are tabulated for thicknesses of 2, 3,/_, and 5 percent chord. Also presented for these thin airfoil sections are theoretical values (_ pressures a_d velocity ratios required to obtain theoretical airfoil pressure distributions.

Patterson smd Albert L. Braslow Basic thicknessforms of the NACA63-, 64-,65-series and NACA63A-, 64A-, 65A-seriesairfoil sectionsare tabulated for thicknesses of 2, 3, 4 4, and 5 percent chord.

后边两位数是厚度，12代表最大厚度为弦长的12%。 63系列翼型相对小众，用的不多，再加上每个厚度都来一个，那profili翼型库得翻倍了。 你要哪个厚度？ 我发你. 或者自己找63翼型的函数，自己生成。 profili可以自己生成NACA翼型啊。 在management下面有一个generate new naca airfoil选项，进去以后选naca 6 series airfoil即可。 另外NACA6系列翼型失速特性普遍不好，你搞一个设计 升力系数 有0.8的翼型，估计 极曲线 会很难看，不建议用这玩意。 如果是做航模级 …

May 31, 2022 · Only a few of these 6A sections were published in the book. I have added those that I know were used on a production airplane. Let the page finish loading before clicking on a section. Go back to the AVD page.

Sep 6, 2013 · Information is presented with which ordinates can be easily obtained for any thickness from 2 to 21 percent chord for NACA 63-, 64-, and 65-series airfoil sections and from 2 to 15 percent chord for NACA 63A-, 64-A, series airfoil sections.

Max thickness 18% at 33.9% chord.

Jan 5, 2009 · It is found that RFOIL predicts the maximum lift coefficient at a Reynolds number of 3 million well, but consistently under predicts the Cl,max for Reynolds numbers of 6 and 9 million.