S1210 12% (s1210-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 100,000 Max Cl/Cd: 59.3 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1210-il-100000.txt Download as CSV file: xf-s1210-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.000 -0.1391 0.09951 0.09554 -0.0491 0.9590 0.1100
-5.750 -0.1437 0.09788 0.09399 -0.0597 0.9378 0.1135
-5.500 -0.1030 0.09237 0.08843 -0.0564 0.9365 0.1183
-5.250 -0.0897 0.09004 0.08612 -0.0714 0.9169 0.1281
-5.000 -0.0680 0.08539 0.08148 -0.0671 0.9103 0.1307
-4.750 -0.0323 0.08146 0.07751 -0.0710 0.9052 0.1393
-4.500 -0.0123 0.07740 0.07347 -0.0772 0.8914 0.1465
-4.250 0.0107 0.07446 0.07051 -0.0789 0.8794 0.1542
-4.000 0.2447 0.03335 0.02743 -0.1804 0.8884 0.0723
-3.750 0.3203 0.02947 0.02275 -0.1914 0.8815 0.0691
-3.500 0.3888 0.02631 0.01910 -0.1994 0.8780 0.0691
-3.250 0.4511 0.02377 0.01636 -0.2053 0.8749 0.0713
-3.000 0.5000 0.02226 0.01491 -0.2090 0.8640 0.0797
-2.750 0.5706 0.02037 0.01296 -0.2168 0.8596 0.0978
-2.500 0.6340 0.02020 0.01342 -0.2231 0.8473 0.3114
-2.250 0.6577 0.02143 0.01489 -0.2196 0.8323 0.3615
-2.000 0.6910 0.02178 0.01522 -0.2189 0.8177 0.3920
-1.750 0.7380 0.02139 0.01458 -0.2222 0.8030 0.4088
-1.500 0.7878 0.02095 0.01383 -0.2266 0.7881 0.4222
-1.250 0.8301 0.02073 0.01336 -0.2294 0.7735 0.4322
-1.000 0.8723 0.02052 0.01290 -0.2323 0.7598 0.4407
-0.750 0.9103 0.02047 0.01262 -0.2345 0.7460 0.4492
-0.500 0.9447 0.02047 0.01245 -0.2359 0.7327 0.4561
-0.250 0.9773 0.02056 0.01242 -0.2370 0.7213 0.4629
0.000 1.0159 0.02062 0.01224 -0.2392 0.7120 0.4718
0.250 1.0435 0.02082 0.01242 -0.2393 0.7011 0.4790
0.500 1.0781 0.02099 0.01243 -0.2408 0.6922 0.4877
0.750 1.1074 0.02121 0.01263 -0.2411 0.6832 0.4966
1.000 1.1389 0.02148 0.01283 -0.2419 0.6758 0.5074
1.250 1.1688 0.02177 0.01310 -0.2424 0.6675 0.5198
1.500 1.2005 0.02204 0.01332 -0.2432 0.6609 0.5324
1.750 1.2266 0.02241 0.01378 -0.2430 0.6532 0.5457
2.000 1.2585 0.02270 0.01402 -0.2437 0.6470 0.5638
2.250 1.2848 0.02315 0.01458 -0.2436 0.6399 0.5838
2.500 1.3125 0.02349 0.01499 -0.2435 0.6335 0.6055
2.750 1.3425 0.02385 0.01536 -0.2439 0.6278 0.6338
3.000 1.3646 0.02432 0.01600 -0.2428 0.6206 0.6640
3.250 1.3920 0.02455 0.01632 -0.2424 0.6145 0.7043
3.500 1.4122 0.02495 0.01691 -0.2408 0.6073 0.7534
3.750 1.4292 0.02505 0.01720 -0.2382 0.6004 0.8270
4.000 1.4486 0.02508 0.01723 -0.2364 0.5946 1.0000
4.250 1.4760 0.02580 0.01798 -0.2368 0.5865 1.0000
4.500 1.5096 0.02620 0.01824 -0.2378 0.5803 1.0000
4.750 1.5315 0.02697 0.01911 -0.2370 0.5724 1.0000
5.000 1.5612 0.02735 0.01944 -0.2372 0.5652 1.0000
5.250 1.5842 0.02799 0.02014 -0.2363 0.5569 1.0000
5.500 1.6131 0.02825 0.02033 -0.2362 0.5485 1.0000
5.750 1.6347 0.02884 0.02104 -0.2351 0.5393 1.0000
6.000 1.6650 0.02897 0.02107 -0.2351 0.5309 1.0000
6.250 1.6839 0.02957 0.02182 -0.2335 0.5209 1.0000
6.500 1.7147 0.02963 0.02177 -0.2336 0.5123 1.0000
6.750 1.7332 0.03010 0.02240 -0.2317 0.5014 1.0000
7.000 1.7564 0.03042 0.02276 -0.2306 0.4915 1.0000
7.250 1.7832 0.03049 0.02279 -0.2301 0.4817 1.0000
7.500 1.8004 0.03096 0.02344 -0.2280 0.4702 1.0000
7.750 1.8232 0.03117 0.02368 -0.2268 0.4595 1.0000
8.000 1.8483 0.03117 0.02364 -0.2258 0.4482 1.0000
8.250 1.8625 0.03159 0.02424 -0.2232 0.4351 1.0000
8.500 1.8784 0.03194 0.02470 -0.2208 0.4219 1.0000
8.750 1.8940 0.03225 0.02509 -0.2183 0.4079 1.0000
9.000 1.9071 0.03260 0.02552 -0.2154 0.3928 1.0000
9.250 1.9165 0.03306 0.02607 -0.2119 0.3762 1.0000
9.500 1.9222 0.03367 0.02676 -0.2078 0.3586 1.0000
9.750 1.9233 0.03446 0.02759 -0.2031 0.3410 1.0000
10.000 1.9224 0.03547 0.02856 -0.1981 0.3237 1.0000
10.250 1.9217 0.03678 0.02978 -0.1936 0.3066 1.0000
10.500 1.9200 0.03850 0.03144 -0.1892 0.2895 1.0000
10.750 1.9196 0.04043 0.03329 -0.1853 0.2738 1.0000
11.000 1.9217 0.04247 0.03524 -0.1820 0.2596 1.0000
11.250 1.9244 0.04459 0.03732 -0.1790 0.2469 1.0000
11.500 1.9263 0.04686 0.03966 -0.1761 0.2355 1.0000
11.750 1.9328 0.04904 0.04181 -0.1738 0.2253 1.0000
12.000 1.9478 0.05083 0.04345 -0.1725 0.2158 1.0000
12.250 1.9488 0.05336 0.04622 -0.1699 0.2085 1.0000
12.500 1.9765 0.05472 0.04738 -0.1698 0.2002 1.0000
12.750 1.9720 0.05756 0.05056 -0.1669 0.1952 1.0000
13.000 1.9814 0.05965 0.05273 -0.1653 0.1891 1.0000
13.250 1.9998 0.06159 0.05468 -0.1646 0.1834 1.0000
13.500 1.9962 0.06460 0.05800 -0.1622 0.1793 1.0000
13.750 2.0064 0.06678 0.06028 -0.1609 0.1746 1.0000
14.000 2.0294 0.06855 0.06205 -0.1606 0.1694 1.0000
14.250 2.0148 0.07241 0.06628 -0.1580 0.1665 1.0000
14.500 2.0078 0.07591 0.07005 -0.1562 0.1631 1.0000
14.750 2.0300 0.07718 0.07125 -0.1556 0.1579 1.0000
15.000 2.0266 0.08079 0.07509 -0.1543 0.1546 1.0000
15.250 2.0057 0.08568 0.08035 -0.1528 0.1523 1.0000
15.500 1.9889 0.09050 0.08548 -0.1520 0.1497 1.0000
15.750 1.9839 0.09403 0.08916 -0.1515 0.1462 1.0000
16.000 2.0068 0.09518 0.09024 -0.1509 0.1412 1.0000
16.250 1.9755 0.10180 0.09727 -0.1513 0.1398 1.0000
16.500 1.9446 0.10906 0.10489 -0.1527 0.1384 1.0000
16.750 1.9125 0.11701 0.11317 -0.1552 0.1369 1.0000
17.000 1.8731 0.12676 0.12325 -0.1594 0.1359 1.0000
17.500 1.8408 0.13956 0.13638 -0.1654 0.1308 1.0000
17.750 1.8052 0.15029 0.14732 -0.1717 0.1297 1.0000
18.000 1.7672 0.16251 0.15970 -0.1793 0.1284 1.0000
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Polar data table (+)
Polar graphs
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