S1210 12% (s1210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.88 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1210-il-1000000-n5.txt Download as CSV file: xf-s1210-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0647 0.09807 0.09628 -0.0822 0.9526 0.0064
-9.000 -0.0492 0.09101 0.08922 -0.0858 0.9389 0.0067
-8.500 -0.1668 0.03998 0.03773 -0.1321 0.9056 0.0078
-8.250 -0.0834 0.02406 0.02118 -0.1770 0.8828 0.0079
-8.000 0.0132 0.01820 0.01478 -0.2035 0.8583 0.0081
-7.750 0.0680 0.01661 0.01283 -0.2123 0.8244 0.0083
-7.500 0.1079 0.01553 0.01142 -0.2168 0.7896 0.0084
-7.250 0.1437 0.01470 0.01030 -0.2198 0.7582 0.0086
-7.000 0.1786 0.01403 0.00939 -0.2223 0.7296 0.0088
-6.750 0.2130 0.01352 0.00866 -0.2244 0.7039 0.0090
-6.500 0.2486 0.01300 0.00790 -0.2267 0.6798 0.0093
-6.250 0.2851 0.01247 0.00717 -0.2291 0.6581 0.0095
-6.000 0.3204 0.01204 0.00656 -0.2311 0.6383 0.0097
-5.750 0.3550 0.01170 0.00606 -0.2328 0.6216 0.0099
-5.500 0.3889 0.01142 0.00565 -0.2343 0.6075 0.0101
-5.250 0.4221 0.01121 0.00531 -0.2356 0.5944 0.0102
-5.000 0.4613 0.01069 0.00466 -0.2385 0.5821 0.0107
-4.750 0.4959 0.01043 0.00431 -0.2401 0.5715 0.0110
-4.500 0.5292 0.01026 0.00405 -0.2413 0.5614 0.0113
-4.250 0.5623 0.01010 0.00380 -0.2425 0.5520 0.0116
-4.000 0.5949 0.00997 0.00359 -0.2435 0.5435 0.0119
-3.750 0.6273 0.00985 0.00340 -0.2444 0.5350 0.0122
-3.500 0.6588 0.00978 0.00325 -0.2451 0.5270 0.0128
-3.250 0.6900 0.00972 0.00313 -0.2457 0.5189 0.0132
-3.000 0.7219 0.00965 0.00297 -0.2465 0.5117 0.0138
-2.750 0.7533 0.00958 0.00285 -0.2472 0.5055 0.0147
-2.500 0.7839 0.00957 0.00278 -0.2476 0.4991 0.0158
-2.250 0.8142 0.00956 0.00273 -0.2480 0.4939 0.0172
-2.000 0.8460 0.00948 0.00267 -0.2488 0.4885 0.0329
-1.750 0.8836 0.00918 0.00258 -0.2512 0.4825 0.1311
-1.500 0.9173 0.00904 0.00263 -0.2525 0.4775 0.2190
-1.250 0.9465 0.00909 0.00268 -0.2527 0.4725 0.2370
-1.000 0.9754 0.00915 0.00274 -0.2528 0.4677 0.2454
-0.750 1.0037 0.00924 0.00278 -0.2527 0.4635 0.2507
-0.500 1.0326 0.00929 0.00283 -0.2528 0.4599 0.2564
-0.250 1.0613 0.00936 0.00289 -0.2528 0.4557 0.2624
0.000 1.0896 0.00945 0.00295 -0.2527 0.4515 0.2658
0.250 1.1177 0.00955 0.00302 -0.2526 0.4475 0.2685
0.500 1.1464 0.00961 0.00308 -0.2526 0.4445 0.2721
0.750 1.1748 0.00969 0.00316 -0.2526 0.4403 0.2762
1.000 1.2027 0.00980 0.00325 -0.2525 0.4349 0.2803
1.250 1.2305 0.00992 0.00334 -0.2524 0.4292 0.2841
1.500 1.2586 0.01001 0.00343 -0.2523 0.4238 0.2886
1.750 1.2865 0.01012 0.00353 -0.2522 0.4193 0.2942
2.000 1.3141 0.01025 0.00365 -0.2520 0.4153 0.2998
2.250 1.3421 0.01033 0.00375 -0.2520 0.4120 0.3057
2.500 1.3699 0.01043 0.00387 -0.2519 0.4063 0.3136
2.750 1.3970 0.01060 0.00401 -0.2516 0.3995 0.3215
3.000 1.4248 0.01069 0.00414 -0.2515 0.3949 0.3310
3.250 1.4520 0.01084 0.00428 -0.2513 0.3873 0.3397
3.500 1.4791 0.01100 0.00443 -0.2511 0.3796 0.3502
3.750 1.5062 0.01115 0.00459 -0.2509 0.3711 0.3612
4.000 1.5331 0.01132 0.00476 -0.2506 0.3636 0.3730
4.250 1.5599 0.01148 0.00493 -0.2504 0.3553 0.3861
4.500 1.5864 0.01169 0.00514 -0.2501 0.3444 0.4004
4.750 1.6119 0.01199 0.00538 -0.2496 0.3264 0.4155
5.000 1.6365 0.01240 0.00570 -0.2490 0.3049 0.4339
5.500 1.6846 0.01332 0.00647 -0.2477 0.2621 0.4735
5.750 1.7082 0.01380 0.00688 -0.2469 0.2433 0.4943
6.000 1.7319 0.01425 0.00729 -0.2462 0.2271 0.5167
6.250 1.7556 0.01470 0.00772 -0.2454 0.2130 0.5412
6.500 1.7790 0.01515 0.00815 -0.2446 0.1998 0.5679
6.750 1.8026 0.01558 0.00859 -0.2439 0.1876 0.5995
7.000 1.8262 0.01602 0.00905 -0.2432 0.1761 0.6400
7.250 1.8492 0.01649 0.00955 -0.2423 0.1647 0.6837
7.500 1.8714 0.01702 0.01010 -0.2413 0.1528 0.7326
7.750 1.8931 0.01757 0.01070 -0.2403 0.1416 0.7992
8.000 1.9066 0.01782 0.01113 -0.2373 0.1350 1.0000
8.250 1.9244 0.01841 0.01169 -0.2354 0.1273 1.0000
8.500 1.9418 0.01897 0.01223 -0.2335 0.1200 1.0000
8.750 1.9576 0.01962 0.01286 -0.2313 0.1125 1.0000
9.000 1.9741 0.02023 0.01346 -0.2292 0.1066 1.0000
9.250 1.9902 0.02089 0.01411 -0.2271 0.1015 1.0000
9.500 2.0069 0.02148 0.01473 -0.2251 0.0979 1.0000
9.750 2.0208 0.02226 0.01550 -0.2227 0.0923 1.0000
10.000 2.0354 0.02301 0.01627 -0.2204 0.0877 1.0000
10.250 2.0501 0.02374 0.01703 -0.2183 0.0846 1.0000
10.500 2.0628 0.02462 0.01791 -0.2158 0.0809 1.0000
10.750 2.0749 0.02556 0.01887 -0.2133 0.0772 1.0000
11.000 2.0884 0.02639 0.01975 -0.2110 0.0749 1.0000
11.250 2.1003 0.02735 0.02075 -0.2086 0.0725 1.0000
11.500 2.1070 0.02872 0.02211 -0.2056 0.0667 1.0000
11.750 2.1164 0.02991 0.02333 -0.2030 0.0626 1.0000
12.000 2.1214 0.03148 0.02490 -0.2000 0.0576 1.0000
12.250 2.1274 0.03303 0.02648 -0.1973 0.0530 1.0000
12.500 2.1316 0.03478 0.02826 -0.1945 0.0489 1.0000
12.750 2.1320 0.03696 0.03045 -0.1916 0.0428 1.0000
13.000 2.1258 0.03989 0.03338 -0.1883 0.0348 1.0000
13.250 2.1181 0.04319 0.03670 -0.1854 0.0281 1.0000
13.500 2.1140 0.04632 0.03988 -0.1832 0.0243 1.0000
13.750 2.1031 0.05048 0.04409 -0.1810 0.0185 1.0000
14.000 2.0891 0.05535 0.04901 -0.1793 0.0132 1.0000
14.250 2.0839 0.05929 0.05304 -0.1783 0.0112 1.0000
14.500 2.0743 0.06406 0.05789 -0.1775 0.0085 1.0000
14.750 2.0616 0.06946 0.06338 -0.1771 0.0058 1.0000
15.000 2.0462 0.07548 0.06950 -0.1770 0.0029 1.0000
15.250 2.0414 0.07999 0.07411 -0.1770 0.0026 1.0000
15.500 2.0285 0.08592 0.08015 -0.1774 0.0016 1.0000
15.750 2.0223 0.09079 0.08512 -0.1778 0.0015 1.0000
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Polar data table (+)
Polar graphs
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