NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Reynolds number: 200,000 Max Cl/Cd: 67.01 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc12b3-il-200000.txt Download as CSV file: xf-rc12b3-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-12(B)3 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3511 0.09922 0.09583 -0.0354 1.0000 0.0654
-10.250 -0.4977 0.09828 0.09477 -0.0364 1.0000 0.0630
-10.000 -0.4837 0.09601 0.09250 -0.0337 1.0000 0.0639
-9.750 -0.4754 0.09319 0.08968 -0.0335 1.0000 0.0649
-9.500 -0.4719 0.08972 0.08624 -0.0348 1.0000 0.0661
-9.250 -0.4735 0.08548 0.08203 -0.0376 1.0000 0.0675
-9.000 -0.4830 0.08032 0.07690 -0.0423 1.0000 0.0687
-8.750 -0.5002 0.07611 0.07269 -0.0439 1.0000 0.0698
-8.500 -0.5313 0.07459 0.07122 -0.0388 1.0000 0.0698
-8.250 -0.5623 0.07334 0.06999 -0.0328 1.0000 0.0699
-8.000 -0.5891 0.07160 0.06823 -0.0277 1.0000 0.0705
-7.500 -0.5871 0.05922 0.05526 -0.0325 0.9876 0.0760
-7.250 -0.5617 0.05677 0.05283 -0.0341 0.9846 0.0781
-7.000 -0.5909 0.03897 0.03342 -0.0283 0.9743 0.0509
-6.750 -0.5704 0.03448 0.02846 -0.0283 0.9708 0.0499
-6.500 -0.5541 0.03112 0.02460 -0.0266 0.9648 0.0498
-6.250 -0.5281 0.02864 0.02158 -0.0264 0.9604 0.0512
-6.000 -0.4967 0.02603 0.01852 -0.0275 0.9578 0.0530
-5.750 -0.4588 0.02436 0.01674 -0.0299 0.9561 0.0551
-5.500 -0.4345 0.02339 0.01563 -0.0293 0.9497 0.0572
-5.250 -0.3998 0.02240 0.01441 -0.0306 0.9461 0.0608
-5.000 -0.3626 0.02097 0.01286 -0.0327 0.9436 0.0650
-4.750 -0.3246 0.02016 0.01200 -0.0348 0.9413 0.0698
-4.500 -0.3011 0.01975 0.01145 -0.0338 0.9340 0.0744
-4.250 -0.2682 0.01882 0.01061 -0.0350 0.9300 0.0815
-4.000 -0.2336 0.01808 0.00980 -0.0363 0.9269 0.0894
-3.750 -0.2102 0.01773 0.00950 -0.0355 0.9199 0.0975
-3.500 -0.1821 0.01715 0.00896 -0.0355 0.9146 0.1073
-3.250 -0.1521 0.01665 0.00846 -0.0357 0.9109 0.1195
-3.000 -0.1313 0.01647 0.00828 -0.0343 0.9027 0.1317
-2.750 -0.1058 0.01595 0.00786 -0.0337 0.8976 0.1488
-2.500 -0.0841 0.01555 0.00760 -0.0324 0.8912 0.1706
-2.250 -0.0631 0.01509 0.00733 -0.0310 0.8842 0.2065
-2.000 0.0310 0.01325 0.00826 -0.0431 0.8883 0.8989
-1.750 0.0761 0.01409 0.00897 -0.0450 0.8841 0.9380
-1.500 0.1396 0.01458 0.00930 -0.0512 0.8816 0.9624
-1.250 0.2142 0.01457 0.00916 -0.0601 0.8795 0.9854
-1.000 0.2829 0.01412 0.00863 -0.0688 0.8737 1.0000
-0.750 0.3036 0.01398 0.00841 -0.0673 0.8656 1.0000
-0.500 0.3263 0.01389 0.00826 -0.0664 0.8565 1.0000
-0.250 0.3474 0.01374 0.00804 -0.0648 0.8490 1.0000
0.000 0.3708 0.01367 0.00792 -0.0641 0.8395 1.0000
0.250 0.3923 0.01351 0.00769 -0.0626 0.8323 1.0000
0.500 0.4162 0.01344 0.00760 -0.0619 0.8222 1.0000
0.750 0.4386 0.01329 0.00739 -0.0606 0.8143 1.0000
1.000 0.4622 0.01319 0.00726 -0.0597 0.8041 1.0000
1.250 0.4857 0.01309 0.00713 -0.0587 0.7945 1.0000
1.500 0.5090 0.01294 0.00693 -0.0576 0.7855 1.0000
1.750 0.5333 0.01288 0.00686 -0.0569 0.7744 1.0000
2.000 0.5573 0.01278 0.00674 -0.0560 0.7644 1.0000
2.250 0.5813 0.01267 0.00658 -0.0550 0.7540 1.0000
2.500 0.6058 0.01262 0.00653 -0.0543 0.7415 1.0000
2.750 0.6300 0.01254 0.00645 -0.0535 0.7285 1.0000
3.000 0.6543 0.01247 0.00635 -0.0526 0.7145 1.0000
3.250 0.6786 0.01241 0.00626 -0.0518 0.6996 1.0000
3.500 0.7031 0.01238 0.00623 -0.0510 0.6842 1.0000
3.750 0.7275 0.01238 0.00620 -0.0502 0.6675 1.0000
4.000 0.7518 0.01239 0.00618 -0.0494 0.6493 1.0000
4.250 0.7759 0.01243 0.00617 -0.0486 0.6292 1.0000
4.500 0.7997 0.01250 0.00621 -0.0478 0.6055 1.0000
4.750 0.8232 0.01262 0.00624 -0.0469 0.5812 1.0000
5.000 0.8464 0.01279 0.00635 -0.0460 0.5541 1.0000
5.250 0.8691 0.01301 0.00651 -0.0450 0.5259 1.0000
5.500 0.8912 0.01330 0.00669 -0.0440 0.4964 1.0000
5.750 0.9126 0.01363 0.00691 -0.0429 0.4656 1.0000
6.000 0.9333 0.01402 0.00720 -0.0418 0.4346 1.0000
6.250 0.9532 0.01445 0.00751 -0.0405 0.4037 1.0000
6.500 0.9723 0.01493 0.00787 -0.0391 0.3732 1.0000
6.750 0.9906 0.01543 0.00826 -0.0376 0.3435 1.0000
7.000 1.0079 0.01598 0.00870 -0.0359 0.3146 1.0000
7.250 1.0245 0.01654 0.00917 -0.0342 0.2860 1.0000
7.500 1.0402 0.01713 0.00967 -0.0323 0.2582 1.0000
7.750 1.0547 0.01777 0.01021 -0.0302 0.2315 1.0000
8.000 1.0676 0.01847 0.01081 -0.0279 0.2065 1.0000
8.250 1.0795 0.01919 0.01143 -0.0254 0.1823 1.0000
8.500 1.0897 0.01998 0.01213 -0.0226 0.1613 1.0000
8.750 1.0988 0.02079 0.01286 -0.0196 0.1426 1.0000
9.000 1.1060 0.02164 0.01364 -0.0163 0.1269 1.0000
9.250 1.1117 0.02249 0.01447 -0.0128 0.1141 1.0000
9.500 1.1139 0.02338 0.01532 -0.0087 0.1041 1.0000
9.750 1.1110 0.02425 0.01613 -0.0037 0.0966 1.0000
10.000 1.1122 0.02507 0.01701 0.0005 0.0896 1.0000
10.250 1.1109 0.02613 0.01801 0.0048 0.0839 1.0000
10.500 1.1147 0.02708 0.01904 0.0082 0.0784 1.0000
10.750 1.1178 0.02809 0.02006 0.0115 0.0736 1.0000
11.000 1.1205 0.02940 0.02137 0.0147 0.0695 1.0000
11.250 1.1266 0.03041 0.02247 0.0174 0.0656 1.0000
11.500 1.1312 0.03158 0.02365 0.0200 0.0622 1.0000
11.750 1.1373 0.03305 0.02513 0.0224 0.0590 1.0000
12.000 1.1439 0.03420 0.02641 0.0247 0.0561 1.0000
12.250 1.1500 0.03544 0.02769 0.0268 0.0535 1.0000
12.500 1.1588 0.03708 0.02927 0.0286 0.0506 1.0000
12.750 1.1649 0.03849 0.03085 0.0306 0.0487 1.0000
13.000 1.1701 0.03996 0.03246 0.0326 0.0466 1.0000
13.250 1.1753 0.04144 0.03402 0.0343 0.0447 1.0000
13.500 1.1824 0.04302 0.03557 0.0358 0.0429 1.0000
13.750 1.1890 0.04516 0.03783 0.0373 0.0411 1.0000
14.000 1.1893 0.04709 0.03997 0.0390 0.0398 1.0000
14.250 1.1907 0.04917 0.04223 0.0405 0.0385 1.0000
14.500 1.1914 0.05132 0.04451 0.0417 0.0373 1.0000
14.750 1.1932 0.05340 0.04667 0.0427 0.0362 1.0000
15.000 1.2006 0.05565 0.04890 0.0436 0.0348 1.0000
15.250 1.1933 0.05902 0.05249 0.0446 0.0341 1.0000
15.500 1.1823 0.06237 0.05609 0.0451 0.0336 1.0000
15.750 1.1706 0.06609 0.06006 0.0452 0.0330 1.0000
16.000 1.1580 0.07018 0.06437 0.0449 0.0325 1.0000
16.250 1.1442 0.07470 0.06911 0.0442 0.0320 1.0000
16.500 1.1286 0.07977 0.07440 0.0429 0.0317 1.0000
16.750 1.1104 0.08550 0.08035 0.0410 0.0315 1.0000
17.000 1.0887 0.09215 0.08722 0.0382 0.0314 1.0000
17.250 1.0621 0.10016 0.09546 0.0343 0.0316 1.0000
17.500 1.0288 0.11004 0.10559 0.0288 0.0319 1.0000
17.750 0.9877 0.12250 0.11829 0.0215 0.0326 1.0000
18.000 0.9395 0.13785 0.13382 0.0124 0.0337 1.0000
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Polar data table (+)
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