S1210 12% (s1210-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 500,000 Max Cl/Cd: 121.45 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1210-il-500000.txt Download as CSV file: xf-s1210-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S1210 12%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.0055 0.09232 0.09018 -0.0753 0.9706 0.0202
-9.000 -0.0093 0.08699 0.08485 -0.0790 0.9653 0.0209
-8.750 0.0011 0.08235 0.08022 -0.0813 0.9624 0.0212
-8.500 0.0205 0.07945 0.07732 -0.0830 0.9606 0.0216
-8.250 0.0347 0.07709 0.07497 -0.0837 0.9558 0.0226
-8.000 0.0455 0.07355 0.07143 -0.0856 0.9509 0.0234
-7.750 0.0500 0.06741 0.06530 -0.0914 0.9479 0.0255
-7.500 0.0496 0.06288 0.06079 -0.0936 0.9387 0.0257
-7.250 0.0625 0.05892 0.05684 -0.0949 0.9349 0.0263
-7.000 0.0706 0.05652 0.05444 -0.0947 0.9244 0.0267
-6.750 0.0870 0.05368 0.05160 -0.0966 0.9177 0.0276
-6.500 0.0994 0.04998 0.04788 -0.0994 0.9077 0.0288
-6.250 0.0964 0.04233 0.04021 -0.1073 0.8943 0.0314
-6.000 0.1134 0.03601 0.03386 -0.1143 0.8825 0.0324
-5.750 0.1516 0.03308 0.03086 -0.1209 0.8689 0.0335
-5.500 0.1836 0.02700 0.02468 -0.1329 0.8510 0.0365
-5.250 0.2829 0.00953 0.00632 -0.1927 0.8517 0.0419
-5.000 0.3410 0.01622 0.01189 -0.2121 0.8790 0.0276
-4.750 0.4201 0.01284 0.00787 -0.2234 0.8650 0.0223
-4.500 0.4898 0.01167 0.00644 -0.2324 0.8402 0.0225
-4.250 0.5426 0.01114 0.00566 -0.2378 0.8061 0.0232
-4.000 0.5807 0.01088 0.00515 -0.2400 0.7712 0.0238
-3.750 0.6137 0.01075 0.00479 -0.2411 0.7400 0.0248
-3.250 0.6808 0.01041 0.00404 -0.2436 0.6884 0.0273
-3.000 0.7126 0.01034 0.00380 -0.2444 0.6674 0.0294
-2.750 0.7442 0.01030 0.00357 -0.2451 0.6488 0.0333
-2.500 0.7889 0.00966 0.00333 -0.2494 0.6314 0.2134
-2.250 0.8165 0.00983 0.00344 -0.2492 0.6169 0.2472
-2.000 0.8437 0.01003 0.00355 -0.2488 0.6043 0.2654
-1.750 0.8710 0.01024 0.00367 -0.2485 0.5931 0.2795
-1.500 0.8989 0.01040 0.00375 -0.2484 0.5826 0.2896
-1.250 0.9267 0.01056 0.00385 -0.2482 0.5734 0.2984
-1.000 0.9548 0.01071 0.00392 -0.2481 0.5645 0.3068
-0.750 0.9833 0.01081 0.00398 -0.2481 0.5564 0.3120
-0.500 1.0117 0.01094 0.00402 -0.2480 0.5489 0.3158
-0.250 1.0402 0.01105 0.00407 -0.2480 0.5424 0.3193
0.000 1.0694 0.01111 0.00413 -0.2482 0.5358 0.3242
0.250 1.0978 0.01128 0.00424 -0.2482 0.5298 0.3294
0.500 1.1264 0.01135 0.00431 -0.2482 0.5242 0.3345
0.750 1.1553 0.01145 0.00440 -0.2483 0.5188 0.3402
1.000 1.1838 0.01163 0.00453 -0.2484 0.5137 0.3467
1.250 1.2123 0.01172 0.00464 -0.2484 0.5090 0.3538
1.500 1.2411 0.01181 0.00477 -0.2485 0.5041 0.3622
1.750 1.2690 0.01198 0.00490 -0.2484 0.4986 0.3717
2.000 1.2972 0.01209 0.00505 -0.2484 0.4928 0.3831
2.250 1.3253 0.01219 0.00518 -0.2484 0.4870 0.3961
2.500 1.3534 0.01236 0.00535 -0.2483 0.4824 0.4108
2.750 1.3818 0.01251 0.00554 -0.2484 0.4782 0.4277
3.000 1.4099 0.01260 0.00572 -0.2484 0.4736 0.4472
3.500 1.4652 0.01293 0.00611 -0.2482 0.4626 0.4939
3.750 1.4928 0.01301 0.00630 -0.2481 0.4574 0.5220
4.000 1.5200 0.01315 0.00650 -0.2479 0.4514 0.5542
4.250 1.5473 0.01332 0.00674 -0.2478 0.4455 0.5913
4.750 1.6017 0.01358 0.00722 -0.2474 0.4342 0.6817
5.000 1.6287 0.01372 0.00750 -0.2472 0.4289 0.7408
5.250 1.6542 0.01377 0.00774 -0.2466 0.4236 0.8241
5.500 1.6687 0.01374 0.00784 -0.2436 0.4185 1.0000
5.750 1.6943 0.01398 0.00807 -0.2431 0.4124 1.0000
6.000 1.7198 0.01417 0.00829 -0.2426 0.4052 1.0000
6.250 1.7441 0.01446 0.00856 -0.2418 0.3984 1.0000
6.500 1.7695 0.01464 0.00879 -0.2413 0.3907 1.0000
6.750 1.7929 0.01495 0.00908 -0.2404 0.3825 1.0000
7.000 1.8173 0.01517 0.00935 -0.2397 0.3724 1.0000
7.250 1.8405 0.01547 0.00965 -0.2388 0.3608 1.0000
7.500 1.8625 0.01583 0.00999 -0.2377 0.3458 1.0000
7.750 1.8826 0.01631 0.01040 -0.2362 0.3257 1.0000
8.000 1.8995 0.01699 0.01097 -0.2342 0.3022 1.0000
8.250 1.9137 0.01785 0.01169 -0.2317 0.2767 1.0000
8.500 1.9273 0.01875 0.01247 -0.2291 0.2532 1.0000
8.750 1.9395 0.01974 0.01335 -0.2263 0.2324 1.0000
9.000 1.9521 0.02072 0.01425 -0.2237 0.2153 1.0000
9.250 1.9646 0.02169 0.01517 -0.2210 0.2000 1.0000
9.750 1.9877 0.02374 0.01715 -0.2156 0.1728 1.0000
10.000 1.9978 0.02486 0.01824 -0.2127 0.1605 1.0000
10.250 2.0076 0.02600 0.01939 -0.2099 0.1509 1.0000
10.500 2.0141 0.02741 0.02077 -0.2066 0.1421 1.0000
10.750 2.0241 0.02856 0.02197 -0.2040 0.1350 1.0000
11.000 2.0280 0.03020 0.02360 -0.2007 0.1282 1.0000
11.250 2.0385 0.03138 0.02486 -0.1983 0.1237 1.0000
11.500 2.0437 0.03300 0.02652 -0.1955 0.1189 1.0000
11.750 2.0451 0.03500 0.02856 -0.1923 0.1145 1.0000
12.000 2.0543 0.03640 0.03007 -0.1903 0.1113 1.0000
12.250 2.0588 0.03828 0.03201 -0.1879 0.1073 1.0000
12.500 2.0585 0.04070 0.03446 -0.1853 0.1035 1.0000
12.750 2.0617 0.04289 0.03674 -0.1832 0.1003 1.0000
13.000 2.0675 0.04490 0.03884 -0.1816 0.0967 1.0000
13.250 2.0676 0.04764 0.04163 -0.1798 0.0929 1.0000
13.500 2.0638 0.05097 0.04503 -0.1781 0.0899 1.0000
13.750 2.0674 0.05356 0.04774 -0.1770 0.0875 1.0000
14.000 2.0698 0.05639 0.05069 -0.1760 0.0852 1.0000
14.250 2.0689 0.05974 0.05415 -0.1751 0.0834 1.0000
14.500 2.0662 0.06348 0.05797 -0.1744 0.0812 1.0000
14.750 2.0591 0.06796 0.06253 -0.1740 0.0786 1.0000
15.000 2.0577 0.07171 0.06639 -0.1737 0.0760 1.0000
15.250 2.0576 0.07532 0.07012 -0.1735 0.0739 1.0000
15.500 2.0543 0.07949 0.07438 -0.1734 0.0710 1.0000
15.750 2.0477 0.08423 0.07920 -0.1736 0.0686 1.0000
16.000 2.0395 0.08930 0.08435 -0.1740 0.0658 1.0000
16.250 2.0388 0.09317 0.08836 -0.1743 0.0637 1.0000
16.500 2.0342 0.09773 0.09300 -0.1748 0.0600 1.0000
16.750 2.0254 0.10303 0.09835 -0.1756 0.0567 1.0000
17.000 2.0213 0.10754 0.10297 -0.1764 0.0530 1.0000
17.250 2.0122 0.11293 0.10839 -0.1775 0.0478 1.0000
17.500 2.0001 0.11889 0.11435 -0.1791 0.0401 1.0000
17.750 1.9904 0.12444 0.11996 -0.1806 0.0354 1.0000
18.000 1.9713 0.13176 0.12725 -0.1832 0.0271 1.0000
18.250 1.9588 0.13792 0.13347 -0.1854 0.0227 1.0000
18.500 1.9428 0.14479 0.14036 -0.1883 0.0174 1.0000
18.750 1.9223 0.15266 0.14826 -0.1920 0.0117 1.0000
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Polar data table (+)
Polar graphs
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