Most sources list the Standard Cirrus airfoil as Wortmann FX S 02-196 mod. Correspondence with Helmut Treiber of Schempp-Hirth has confirmed that the inner wing, from the root to the inboard end of the aileron, is a linear transition zone from Wortmann FX S 02-196 to Wortmann FX 66-17 A II-182. From the inboard end of the aileron to the tip the airfoil remains constant as Wortmann FX 66-17 A II-182.

Root Rib Station: FX S 02-196

from Schempp-Hirth Chord Upper Lower 1 1.00000 .00000 .00000 2 .99893 .00026 .00019 3 .99572 .00106 .00069 4 .99039 .00234 .00146 5 .98296 .00411 .00233 6 .97347 .00637 .00318 7 .96194 .00912 .00386 8 .94844 .01238 .00429 9 .93301 .01616 .00439 10 .91573 .02048 .00412 11 .89668 .02535 .00346 12 .87592 .03076 .00238 13 .85355 .03671 .00085 14 .82967 .04314 -.00117 15 .80438 .05000 -.00367 16 .77779 .05722 -.00666 17 .75000 .06469 -.01012 18 .72114 .07234 -.01403 19 .69134 .08007 -.01837 20 .66072 .08779 -.02308 21 .62941 .09539 -.02811 22 .59755 .10276 -.03335 23 .56526 .10977 -.03871 24 .53270 .11628 -.04405 25 .50000 .12212 -.04922 26 .46730 .12703 -.05395 27 .43474 .13068 -.05793 28 .40245 .13280 -.06083 29 .37059 .13327 -.06255 30 .33928 .13218 -.06317 31 .30866 .12981 -.06292 32 .27886 .12639 -.06198 33 .25000 .12207 -.06048 34 .22221 .11695 -.05846 35 .19562 .11108 -.05599 36 .17033 .10455 -.05312 37 .14645 .09747 -.04992 38 .12408 .08993 -.04646 39 .10332 .08202 -.04280 40 .08427 .07384 -.03898 41 .06699 .06540 -.03504 42 .05156 .05679 -.03098 43 .03806 .04822 -.02682 44 .02653 .03996 -.02256 45 .01704 .03201 -.01827 46 .00961 .02395 -.01410 47 .00428 .01553 -.01004 48 .00107 .00723 -.00561 49 .00000 .00000 .00000 DICKE/T = .196 RUECKLAGE/T = .371 WOELBUNG/T = .037 RUECKLAGE/T = .467 PROFILTIEFE = T

Outer Panel: FX 66-17 A II-182

from Schempp-Hirth Chord Upper Lower 1 1.00000 .00000 .00000 2 .99893 .00016 .00016 3 .99572 .00105 .00036 4 .99039 .00263 .00051 5 .98296 .00484 .00062 6 .97347 .00755 .00068 7 .96194 .01062 .00069 8 .94844 .01391 .00065 9 .93301 .01754 .00047 10 .91573 .02151 .00013 11 .89668 .02578 -.00035 12 .87592 .03038 -.00105 13 .85355 .03534 -.00203 14 .82967 .04076 -.00341 15 .80438 .04662 -.00522 16 .77779 .05282 -.00744 17 .75000 .05934 -.01011 18 .72114 .06614 -.01327 19 .69134 .07316 -.01695 20 .66072 .08032 -.02114 21 .62941 .08755 -.02579 22 .59755 .09477 -.03073 23 .56526 .10189 -.03574 24 .53270 .10876 -.04046 25 .50000 .11512 -.04460 26 .46730 .12061 -.04792 27 .43474 .12488 -.05036 28 .40245 .12770 -.05198 29 .37059 .12897 -.05290 30 .33928 .12873 -.05319 31 .30866 .12706 -.05293 32 .27886 .12405 -.05218 33 .25000 .11985 -.05099 34 .22221 .11461 -.04943 35 .19562 .10851 -.04753 36 .17033 .10169 -.04531 37 .14645 .09426 -.04281 38 .12408 .08635 -.04004 39 .10332 .07805 -.03702 40 .08427 .06948 -.03379 41 .06699 .06076 -.03035 42 .05156 .05201 -.02674 43 .03806 .04339 -.02295 44 .02653 .03490 -.01911 45 .01704 .02665 -.01528 46 .00961 .01902 -.01137 47 .00428 .01201 -.00759 48 .00107 .00584 -.00373 49 .00000 .00069 .00069 DICKE/T... = .182 RUECKLAGE/T = .339 WOELBUNG/T = .038 RUECKLAGE/T = .371 PROFILTIEFE = T

Comparison of Root and Outer Airfoils

Lower Section: NACA 63-013A

from UIUC Chord Upper Lower 0.0000000 0.0000000 0.0000000 0.0021329 0.0072069 -0.0072069 0.0085134 0.0134888 -0.0134888 0.0190871 0.0196337 -0.0196337 0.0337638 0.0259275 -0.0259275 0.0524183 0.0320835 -0.0320835 0.0748914 0.0379347 -0.0379347 0.1009914 0.0434546 -0.0434546 0.1304955 0.0485335 -0.0485335 0.1631522 0.0531645 -0.0531645 0.1986827 0.0571469 -0.0571469 0.2367839 0.0604450 -0.0604450 0.2771308 0.0629452 -0.0629452 0.3193792 0.0644979 -0.0644979 0.3631685 0.0649735 -0.0649735 0.4081253 0.0643311 -0.0643311 0.4538658 0.0625567 -0.0625567 0.5000000 0.0597675 -0.0597675 0.5461342 0.0561118 -0.0561118 0.5918748 0.0517576 -0.0517576 0.6368315 0.0468739 -0.0468739 0.6806208 0.0416493 -0.0416493 0.7228692 0.0363058 -0.0363058 0.7632161 0.0310703 -0.0310703 0.8013173 0.0261105 -0.0261105 0.8368478 0.0214922 -0.0214922 0.8695045 0.0172418 -0.0172418 0.8990086 0.0133999 -0.0133999 0.9251086 0.0100067 -0.0100067 0.9475816 0.0070852 -0.0070852 0.9662361 0.0046601 -0.0046601 0.9809128 0.0027521 -0.0027521 0.9914865 0.0013775 -0.0013775 0.9978671 0.0005481 -0.0005481 1.0000000 0.0002708 -0.0002708

Upper Section: NACA 63-012A

from UIUC Chord Upper Lower 0.0000000 0.0000000 0.0000000 0.0021329 0.0066525 -0.0066525 0.0085134 0.0124512 -0.0124512 0.0190871 0.0181234 -0.0181234 0.0337638 0.0239331 -0.0239331 0.0524183 0.0296155 -0.0296155 0.0748914 0.0350166 -0.0350166 0.1009914 0.0401119 -0.0401119 0.1304955 0.0448002 -0.0448002 0.1631522 0.0490749 -0.0490749 0.1986827 0.0527510 -0.0527510 0.2367839 0.0557954 -0.0557954 0.2771308 0.0581033 -0.0581033 0.3193792 0.0595365 -0.0595365 0.3631685 0.0599755 -0.0599755 0.4081253 0.0593826 -0.0593826 0.4538658 0.0577446 -0.0577446 0.5000000 0.0551700 -0.0551700 0.5461342 0.0517955 -0.0517955 0.5918748 0.0477762 -0.0477762 0.6368315 0.0432682 -0.0432682 0.6806208 0.0384455 -0.0384455 0.7228692 0.0335131 -0.0335131 0.7632161 0.0286803 -0.0286803 0.8013173 0.0241020 -0.0241020 0.8368478 0.0198390 -0.0198390 0.8695045 0.0159155 -0.0159155 0.8990086 0.0123691 -0.0123691 0.9251086 0.0092369 -0.0092369 0.9475816 0.0065402 -0.0065402 0.9662361 0.0043016 -0.0043016 0.9809128 0.0025404 -0.0025404 0.9914865 0.0012716 -0.0012716 0.9978671 0.0005059 -0.0005059 1.0000000 0.0002500 -0.0002500

NACA 65-012

from SNACK software Chord Upper Lower 0.0000000 0.0000000 0.0000000 0.0021329 0.0063708 -0.0063708 0.0085135 0.0117272 -0.0117272 0.0190872 0.0165370 -0.0165370 0.0337639 0.0215325 -0.0215325 0.0524184 0.0266663 -0.0266663 0.0748914 0.0316979 -0.0316979 0.1009914 0.0366388 -0.0366388 0.1304955 0.0413017 -0.0413017 0.1631522 0.0456862 -0.0456862 0.1986827 0.0496192 -0.0496192 0.2367839 0.0530509 -0.0530509 0.2771308 0.0558906 -0.0558906 0.3193792 0.0580574 -0.0580574 0.3631685 0.0594629 -0.0594629 0.4081253 0.0599841 -0.0599841 0.4538658 0.0593927 -0.0593927 0.5000000 0.0575700 -0.0575700 0.5461342 0.0544334 -0.0544334 0.5918748 0.0502649 -0.0502649 0.6368315 0.0453704 -0.0453704 0.6806208 0.0399743 -0.0399743 0.7228692 0.0343492 -0.0343492 0.7632161 0.0287178 -0.0287178 0.8013173 0.0232599 -0.0232599 0.8368478 0.0181590 -0.0181590 0.8695045 0.0136357 -0.0136357 0.8990086 0.0096054 -0.0096054 0.9251086 0.0065022 -0.0065022 0.9475816 0.0038459 -0.0038459 0.9662361 0.0024040 -0.0024040 0.9809128 0.0013590 -0.0013590 0.9914865 0.0006062 -0.0006062 0.9978671 0.0001519 -0.0001519 1.0000000 0.0000000 0.0000000