In 1978, J. H. M. Gooden conducted an experimental study of the Wortmann FX 66-S-196 V1 airfoil in the Low-Speed, Low-Turbulence Wind Tunnel at Delft University. His report was published at the XVI OSTIV Congress of 1978 and is available in PDF format here. As can be seen in the image below (when enlarged), the FX 66-S-196 V1 is very similar to the root airfoil used on the Standard Cirrus. For all practical purposes, this study is applicable to the Standard Cirrus wing. Even if you are not technically versed in aerodynamics, you will glean from this well written paper useful insights into the handling and performance of your glider.  (Download PDF Report)

(click to enlarge)

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 All-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