S1210 12% (s1210-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 200,000 Max Cl/Cd: 86.32 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1210-il-200000.txt Download as CSV file: xf-s1210-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1522 0.10650 0.10334 -0.0472 0.9821 0.0446
-7.500 -0.1418 0.10289 0.09974 -0.0560 0.9744 0.0470
-7.250 -0.1336 0.09908 0.09596 -0.0648 0.9649 0.0475
-7.000 -0.1041 0.09416 0.09103 -0.0628 0.9637 0.0491
-6.750 -0.0772 0.09084 0.08770 -0.0659 0.9603 0.0512
-6.500 -0.0614 0.08763 0.08450 -0.0690 0.9516 0.0535
-6.250 -0.0571 0.08411 0.08101 -0.0761 0.9386 0.0572
-6.000 -0.0469 0.07849 0.07543 -0.0829 0.9273 0.0587
-5.750 -0.0209 0.07590 0.07282 -0.0821 0.9233 0.0603
-5.500 0.0099 0.07271 0.06962 -0.0861 0.9197 0.0658
-5.000 0.0454 0.06393 0.06087 -0.0969 0.8952 0.0734
-4.750 0.0786 0.06039 0.05730 -0.1021 0.8904 0.0787
-4.500 0.2838 0.02417 0.01915 -0.1912 0.8914 0.0449
-4.250 0.3625 0.01990 0.01396 -0.2029 0.8891 0.0398
-4.000 0.4117 0.01807 0.01192 -0.2073 0.8782 0.0404
-3.750 0.4649 0.01663 0.01038 -0.2123 0.8678 0.0431
-3.500 0.5260 0.01515 0.00878 -0.2187 0.8564 0.0443
-3.250 0.5922 0.01406 0.00755 -0.2263 0.8388 0.0470
-3.000 0.6633 0.01311 0.00640 -0.2355 0.8150 0.0557
-2.750 0.7298 0.01233 0.00587 -0.2441 0.7873 0.2664
-2.500 0.7639 0.01284 0.00613 -0.2449 0.7606 0.2941
-2.250 0.7915 0.01347 0.00659 -0.2444 0.7364 0.3217
-2.000 0.8176 0.01397 0.00700 -0.2435 0.7163 0.3410
-1.750 0.8469 0.01426 0.00704 -0.2436 0.6986 0.3525
-1.500 0.8756 0.01434 0.00700 -0.2436 0.6829 0.3578
-1.250 0.9047 0.01447 0.00698 -0.2437 0.6689 0.3639
-1.000 0.9354 0.01462 0.00689 -0.2442 0.6567 0.3698
-0.750 0.9649 0.01472 0.00690 -0.2444 0.6463 0.3747
-0.500 0.9937 0.01482 0.00693 -0.2446 0.6357 0.3797
-0.250 1.0245 0.01500 0.00692 -0.2451 0.6269 0.3857
0.000 1.0530 0.01509 0.00700 -0.2451 0.6177 0.3913
0.250 1.0830 0.01528 0.00710 -0.2455 0.6103 0.3979
0.500 1.1122 0.01541 0.00718 -0.2457 0.6026 0.4047
0.750 1.1423 0.01562 0.00732 -0.2461 0.5964 0.4117
1.000 1.1708 0.01577 0.00747 -0.2462 0.5893 0.4204
1.250 1.1998 0.01593 0.00766 -0.2464 0.5831 0.4296
1.500 1.2298 0.01617 0.00786 -0.2468 0.5777 0.4409
1.750 1.2580 0.01634 0.00808 -0.2468 0.5715 0.4537
2.000 1.2874 0.01654 0.00829 -0.2470 0.5661 0.4677
2.250 1.3172 0.01680 0.00856 -0.2474 0.5612 0.4842
2.500 1.3448 0.01697 0.00885 -0.2473 0.5551 0.5031
2.750 1.3736 0.01715 0.00907 -0.2474 0.5490 0.5252
3.000 1.4016 0.01738 0.00938 -0.2474 0.5427 0.5530
3.250 1.4291 0.01754 0.00967 -0.2473 0.5362 0.5847
3.500 1.4583 0.01777 0.00995 -0.2474 0.5312 0.6218
3.750 1.4853 0.01799 0.01035 -0.2472 0.5259 0.6670
4.000 1.5105 0.01813 0.01067 -0.2465 0.5199 0.7224
4.250 1.5332 0.01822 0.01085 -0.2452 0.5144 0.8020
4.500 1.5442 0.01812 0.01095 -0.2413 0.5085 1.0000
4.750 1.5714 0.01836 0.01117 -0.2412 0.5014 1.0000
5.000 1.5991 0.01868 0.01142 -0.2411 0.4951 1.0000
5.250 1.6234 0.01890 0.01171 -0.2404 0.4873 1.0000
5.500 1.6507 0.01919 0.01190 -0.2402 0.4806 1.0000
5.750 1.6736 0.01944 0.01227 -0.2392 0.4729 1.0000
6.000 1.6991 0.01969 0.01249 -0.2386 0.4659 1.0000
6.250 1.7227 0.01999 0.01286 -0.2378 0.4586 1.0000
6.500 1.7463 0.02023 0.01314 -0.2369 0.4508 1.0000
6.750 1.7694 0.02054 0.01350 -0.2359 0.4431 1.0000
7.000 1.7917 0.02081 0.01382 -0.2347 0.4349 1.0000
7.250 1.8134 0.02112 0.01421 -0.2335 0.4261 1.0000
7.500 1.8343 0.02141 0.01451 -0.2321 0.4166 1.0000
7.750 1.8530 0.02172 0.01495 -0.2302 0.4057 1.0000
8.000 1.8717 0.02207 0.01536 -0.2284 0.3945 1.0000
8.250 1.8888 0.02247 0.01578 -0.2263 0.3824 1.0000
8.500 1.9041 0.02290 0.01629 -0.2239 0.3680 1.0000
8.750 1.9168 0.02343 0.01688 -0.2210 0.3514 1.0000
9.000 1.9259 0.02406 0.01756 -0.2175 0.3317 1.0000
9.250 1.9314 0.02497 0.01842 -0.2134 0.3098 1.0000
9.500 1.9346 0.02618 0.01954 -0.2092 0.2878 1.0000
9.750 1.9364 0.02765 0.02092 -0.2050 0.2662 1.0000
10.000 1.9364 0.02938 0.02256 -0.2008 0.2475 1.0000
10.250 1.9360 0.03124 0.02436 -0.1967 0.2315 1.0000
10.500 1.9361 0.03320 0.02628 -0.1929 0.2172 1.0000
10.750 1.9371 0.03519 0.02830 -0.1895 0.2051 1.0000
11.000 1.9370 0.03735 0.03049 -0.1862 0.1951 1.0000
11.250 1.9354 0.03976 0.03287 -0.1830 0.1867 1.0000
11.500 1.9376 0.04196 0.03517 -0.1805 0.1788 1.0000
11.750 1.9361 0.04460 0.03781 -0.1778 0.1724 1.0000
12.000 1.9381 0.04704 0.04034 -0.1756 0.1666 1.0000
12.250 1.9395 0.04960 0.04298 -0.1737 0.1611 1.0000
12.500 1.9391 0.05249 0.04581 -0.1717 0.1563 1.0000
12.750 1.9427 0.05499 0.04852 -0.1702 0.1521 1.0000
13.000 1.9454 0.05766 0.05131 -0.1688 0.1480 1.0000
13.250 1.9485 0.06039 0.05404 -0.1675 0.1444 1.0000
13.500 1.9540 0.06290 0.05660 -0.1662 0.1408 1.0000
13.750 1.9558 0.06584 0.05974 -0.1652 0.1374 1.0000
14.000 1.9567 0.06891 0.06293 -0.1644 0.1336 1.0000
14.250 1.9609 0.07162 0.06564 -0.1635 0.1304 1.0000
14.500 1.9628 0.07467 0.06880 -0.1628 0.1266 1.0000
14.750 1.9602 0.07836 0.07270 -0.1626 0.1232 1.0000
15.000 1.9580 0.08203 0.07649 -0.1625 0.1195 1.0000
15.250 1.9605 0.08503 0.07943 -0.1621 0.1155 1.0000
15.500 1.9556 0.08928 0.08390 -0.1624 0.1123 1.0000
15.750 1.9543 0.09304 0.08784 -0.1627 0.1096 1.0000
16.000 1.9503 0.09723 0.09216 -0.1634 0.1061 1.0000
16.250 1.9514 0.10050 0.09542 -0.1636 0.1029 1.0000
16.500 1.9496 0.10441 0.09948 -0.1642 0.1000 1.0000
16.750 1.9445 0.10901 0.10430 -0.1654 0.0972 1.0000
17.000 1.9400 0.11352 0.10895 -0.1668 0.0940 1.0000
17.250 1.9379 0.11750 0.11297 -0.1679 0.0909 1.0000
17.500 1.9341 0.12188 0.11747 -0.1694 0.0876 1.0000
17.750 1.9296 0.12658 0.12239 -0.1712 0.0850 1.0000
18.000 1.9236 0.13163 0.12759 -0.1735 0.0816 1.0000
18.250 1.9200 0.13601 0.13200 -0.1754 0.0786 1.0000
18.500 1.9166 0.14048 0.13660 -0.1773 0.0758 1.0000
18.750 1.9096 0.14595 0.14230 -0.1802 0.0724 1.0000
19.000 1.9032 0.15123 0.14770 -0.1831 0.0690 1.0000
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Polar data table (+)
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