S1210 12% (s1210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.98 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1210-il-1000000.txt Download as CSV file: xf-s1210-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0031 0.09748 0.09585 -0.0804 0.9737 0.0108
-10.000 0.0085 0.09406 0.09244 -0.0826 0.9723 0.0110
-9.750 -0.1001 0.10687 0.10516 -0.0720 0.9814 0.0106
-9.500 -0.0828 0.10406 0.10235 -0.0748 0.9805 0.0108
-9.250 -0.0654 0.10097 0.09926 -0.0781 0.9797 0.0111
-7.750 -0.0035 0.07619 0.07452 -0.0969 0.9604 0.0137
-7.500 0.0032 0.07379 0.07213 -0.0974 0.9529 0.0138
-7.250 0.0191 0.07135 0.06970 -0.0998 0.9482 0.0141
-7.000 0.0262 0.06954 0.06789 -0.0997 0.9373 0.0145
-6.750 0.0385 0.06619 0.06454 -0.1027 0.9274 0.0150
-6.500 0.0572 0.06118 0.05950 -0.1093 0.9165 0.0157
-6.250 0.1532 0.02371 0.02125 -0.1898 0.8933 0.0179
-5.750 0.3406 0.01317 0.00919 -0.2289 0.8528 0.0158
-5.500 0.3910 0.01202 0.00765 -0.2344 0.8154 0.0157
-5.250 0.4287 0.01121 0.00652 -0.2368 0.7786 0.0154
-5.000 0.4619 0.01068 0.00573 -0.2382 0.7458 0.0154
-4.750 0.4948 0.01032 0.00517 -0.2394 0.7166 0.0156
-4.500 0.5276 0.01007 0.00474 -0.2405 0.6914 0.0160
-4.250 0.5605 0.00987 0.00438 -0.2417 0.6689 0.0164
-4.000 0.5930 0.00973 0.00409 -0.2427 0.6490 0.0167
-3.750 0.6274 0.00952 0.00373 -0.2442 0.6310 0.0170
-3.500 0.6630 0.00929 0.00334 -0.2459 0.6146 0.0176
-3.250 0.6958 0.00918 0.00312 -0.2470 0.6000 0.0185
-3.000 0.7274 0.00912 0.00297 -0.2477 0.5873 0.0197
-2.750 0.7585 0.00909 0.00284 -0.2483 0.5759 0.0207
-2.500 0.7900 0.00905 0.00272 -0.2490 0.5651 0.0236
-2.250 0.8274 0.00875 0.00256 -0.2512 0.5554 0.0941
-2.000 0.8640 0.00851 0.00257 -0.2534 0.5457 0.2220
-1.750 0.8931 0.00856 0.00262 -0.2534 0.5374 0.2395
-1.500 0.9209 0.00870 0.00270 -0.2533 0.5290 0.2540
-1.250 0.9495 0.00877 0.00277 -0.2533 0.5219 0.2655
-1.000 0.9776 0.00889 0.00282 -0.2531 0.5149 0.2714
-0.750 1.0066 0.00895 0.00288 -0.2532 0.5089 0.2777
-0.500 1.0348 0.00904 0.00294 -0.2531 0.5028 0.2829
-0.250 1.0627 0.00917 0.00300 -0.2530 0.4965 0.2874
0.000 1.0921 0.00921 0.00305 -0.2532 0.4918 0.2920
0.250 1.1206 0.00929 0.00312 -0.2532 0.4867 0.2965
0.500 1.1484 0.00943 0.00320 -0.2530 0.4815 0.3006
0.750 1.1771 0.00949 0.00327 -0.2531 0.4770 0.3052
1.000 1.2057 0.00956 0.00335 -0.2531 0.4715 0.3112
1.250 1.2333 0.00971 0.00345 -0.2529 0.4652 0.3170
1.500 1.2618 0.00978 0.00354 -0.2530 0.4606 0.3240
1.750 1.2902 0.00986 0.00363 -0.2529 0.4563 0.3322
2.000 1.3181 0.00997 0.00375 -0.2529 0.4521 0.3411
2.250 1.3456 0.01013 0.00389 -0.2527 0.4474 0.3515
2.500 1.3742 0.01017 0.00399 -0.2528 0.4431 0.3639
2.750 1.4021 0.01028 0.00412 -0.2527 0.4378 0.3780
3.000 1.4295 0.01044 0.00427 -0.2525 0.4326 0.3934
3.250 1.4576 0.01051 0.00440 -0.2525 0.4279 0.4103
3.500 1.4854 0.01062 0.00453 -0.2524 0.4221 0.4289
3.750 1.5125 0.01079 0.00471 -0.2522 0.4166 0.4490
4.000 1.5404 0.01088 0.00486 -0.2522 0.4124 0.4709
4.250 1.5683 0.01098 0.00503 -0.2521 0.4082 0.4955
4.500 1.5955 0.01112 0.00521 -0.2520 0.4029 0.5219
4.750 1.6228 0.01127 0.00541 -0.2518 0.3974 0.5514
5.000 1.6507 0.01137 0.00559 -0.2518 0.3918 0.5866
5.250 1.6779 0.01154 0.00582 -0.2517 0.3854 0.6261
5.500 1.7055 0.01166 0.00604 -0.2516 0.3794 0.6705
5.750 1.7328 0.01182 0.00627 -0.2515 0.3712 0.7229
6.000 1.7598 0.01197 0.00653 -0.2513 0.3624 0.7909
6.250 1.7787 0.01202 0.00675 -0.2494 0.3513 0.9432
6.500 1.8020 0.01230 0.00698 -0.2484 0.3360 1.0000
6.750 1.8254 0.01273 0.00730 -0.2476 0.3149 1.0000
7.000 1.8470 0.01333 0.00776 -0.2465 0.2899 1.0000
7.250 1.8677 0.01399 0.00827 -0.2452 0.2643 1.0000
7.500 1.8878 0.01469 0.00883 -0.2438 0.2411 1.0000
7.750 1.9078 0.01535 0.00939 -0.2424 0.2218 1.0000
8.000 1.9277 0.01598 0.00994 -0.2409 0.2061 1.0000
8.250 1.9465 0.01665 0.01052 -0.2392 0.1905 1.0000
8.500 1.9634 0.01736 0.01115 -0.2372 0.1750 1.0000
8.750 1.9790 0.01809 0.01181 -0.2349 0.1605 1.0000
9.000 1.9945 0.01878 0.01246 -0.2326 0.1493 1.0000
9.250 2.0095 0.01949 0.01314 -0.2303 0.1398 1.0000
9.500 2.0239 0.02027 0.01387 -0.2279 0.1303 1.0000
9.750 2.0389 0.02100 0.01459 -0.2256 0.1222 1.0000
10.000 2.0513 0.02188 0.01545 -0.2230 0.1142 1.0000
10.250 2.0664 0.02259 0.01618 -0.2208 0.1095 1.0000
10.500 2.0784 0.02352 0.01710 -0.2181 0.1039 1.0000
10.750 2.0920 0.02433 0.01795 -0.2158 0.1000 1.0000
11.000 2.1044 0.02523 0.01886 -0.2133 0.0957 1.0000
11.250 2.1146 0.02630 0.01995 -0.2106 0.0915 1.0000
11.500 2.1254 0.02734 0.02102 -0.2081 0.0872 1.0000
11.750 2.1354 0.02845 0.02215 -0.2055 0.0834 1.0000
12.000 2.1427 0.02980 0.02352 -0.2027 0.0794 1.0000
12.250 2.1513 0.03108 0.02485 -0.2001 0.0765 1.0000
12.500 2.1609 0.03230 0.02614 -0.1978 0.0747 1.0000
12.750 2.1678 0.03379 0.02768 -0.1953 0.0718 1.0000
13.000 2.1712 0.03565 0.02956 -0.1926 0.0681 1.0000
13.250 2.1763 0.03743 0.03140 -0.1902 0.0653 1.0000
13.500 2.1814 0.03926 0.03330 -0.1881 0.0627 1.0000
13.750 2.1796 0.04189 0.03593 -0.1855 0.0575 1.0000
14.000 2.1800 0.04444 0.03854 -0.1835 0.0529 1.0000
14.250 2.1763 0.04758 0.04170 -0.1815 0.0482 1.0000
14.500 2.1696 0.05129 0.04544 -0.1797 0.0418 1.0000
14.750 2.1488 0.05702 0.05116 -0.1779 0.0322 1.0000
15.000 2.1272 0.06333 0.05750 -0.1768 0.0240 1.0000
15.250 2.1196 0.06791 0.06216 -0.1763 0.0219 1.0000
15.500 2.0948 0.07527 0.06957 -0.1762 0.0153 1.0000
15.750 2.0793 0.08142 0.07582 -0.1764 0.0122 1.0000
16.000 2.0589 0.08853 0.08302 -0.1770 0.0082 1.0000
16.250 2.0418 0.09523 0.08981 -0.1778 0.0056 1.0000
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Polar data table (+)
Polar graphs
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