NACA 6412 (naca6412-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 6412 (naca6412-il) Reynolds number: 200,000 Max Cl/Cd: 79.99 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca6412-il-200000.txt Download as CSV file: xf-naca6412-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6412
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1668 0.08960 0.08612 -0.0733 0.9635 0.0672
-7.750 -0.1641 0.08548 0.08200 -0.0833 0.9536 0.0713
-7.500 -0.1520 0.07897 0.07549 -0.0933 0.9452 0.0728
-7.250 -0.1249 0.07680 0.07330 -0.0911 0.9442 0.0743
-7.000 -0.0951 0.07338 0.06986 -0.0957 0.9424 0.0770
-6.750 -0.0779 0.06385 0.06012 -0.1193 0.9279 0.0837
-6.500 -0.0530 0.06111 0.05743 -0.1181 0.9269 0.0848
-6.250 -0.0552 0.04110 0.03671 -0.1339 0.9129 0.0632
-6.000 -0.0258 0.03333 0.02830 -0.1398 0.9103 0.0604
-5.750 -0.0160 0.02910 0.02351 -0.1388 0.8995 0.0602
-5.500 0.0168 0.02553 0.01914 -0.1410 0.8965 0.0619
-5.250 0.0521 0.02358 0.01704 -0.1430 0.8944 0.0648
-5.000 0.0715 0.02283 0.01618 -0.1414 0.8850 0.0671
-4.750 0.1053 0.02132 0.01430 -0.1425 0.8812 0.0705
-4.500 0.1409 0.01993 0.01274 -0.1439 0.8784 0.0749
-4.250 0.1636 0.01949 0.01224 -0.1427 0.8697 0.0791
-4.000 0.1960 0.01850 0.01100 -0.1433 0.8650 0.0842
-3.750 0.2309 0.01774 0.01026 -0.1444 0.8615 0.0910
-3.500 0.2541 0.01727 0.00965 -0.1432 0.8519 0.0969
-3.250 0.2864 0.01660 0.00900 -0.1438 0.8467 0.1050
-3.000 0.3136 0.01607 0.00840 -0.1434 0.8390 0.1133
-2.750 0.3429 0.01568 0.00797 -0.1433 0.8316 0.1229
-2.500 0.3724 0.01517 0.00747 -0.1434 0.8246 0.1335
-2.250 0.3994 0.01476 0.00703 -0.1429 0.8155 0.1450
-2.000 0.4287 0.01447 0.00668 -0.1428 0.8078 0.1587
-1.750 0.4557 0.01419 0.00641 -0.1425 0.7984 0.1744
-1.500 0.4834 0.01393 0.00616 -0.1422 0.7896 0.1921
-1.250 0.5114 0.01366 0.00589 -0.1419 0.7802 0.2116
-1.000 0.5373 0.01345 0.00574 -0.1414 0.7697 0.2328
-0.750 0.5667 0.01321 0.00551 -0.1414 0.7611 0.2584
-0.500 0.5912 0.01309 0.00545 -0.1406 0.7495 0.2858
-0.250 0.6182 0.01291 0.00533 -0.1403 0.7397 0.3198
0.000 0.6441 0.01267 0.00521 -0.1398 0.7293 0.3641
0.250 0.6667 0.01228 0.00521 -0.1387 0.7183 0.4649
0.500 0.7208 0.01120 0.00511 -0.1439 0.7093 0.9999
0.750 0.7460 0.01134 0.00512 -0.1432 0.6978 0.9999
1.000 0.7725 0.01149 0.00512 -0.1428 0.6877 0.9999
1.250 0.7997 0.01164 0.00511 -0.1425 0.6781 0.9999
1.500 0.8250 0.01182 0.00522 -0.1420 0.6680 0.9999
1.750 0.8532 0.01200 0.00522 -0.1419 0.6597 0.9999
2.000 0.8775 0.01220 0.00538 -0.1412 0.6496 0.9999
2.250 0.9054 0.01240 0.00545 -0.1411 0.6420 0.9999
2.500 0.9299 0.01261 0.00564 -0.1405 0.6328 0.9999
2.750 0.9581 0.01284 0.00572 -0.1405 0.6256 0.9999
3.000 0.9820 0.01306 0.00596 -0.1397 0.6170 0.9999
3.250 1.0096 0.01329 0.00609 -0.1396 0.6101 0.9999
3.500 1.0342 0.01354 0.00635 -0.1391 0.6024 0.9999
3.750 1.0606 0.01377 0.00654 -0.1388 0.5954 0.9999
4.000 1.0869 0.01405 0.00677 -0.1385 0.5888 0.9999
4.250 1.1117 0.01430 0.00703 -0.1380 0.5816 0.9999
4.500 1.1397 0.01457 0.00723 -0.1380 0.5756 0.9999
4.750 1.1630 0.01485 0.00757 -0.1373 0.5684 0.9999
5.000 1.1890 0.01511 0.00781 -0.1370 0.5619 0.9999
5.250 1.2155 0.01542 0.00810 -0.1368 0.5560 0.9999
5.500 1.2388 0.01570 0.00844 -0.1360 0.5488 0.9999
5.750 1.2659 0.01597 0.00867 -0.1359 0.5427 0.9999
6.000 1.2893 0.01630 0.00908 -0.1352 0.5361 0.9999
6.250 1.3138 0.01658 0.00940 -0.1346 0.5294 0.9999
6.500 1.3403 0.01690 0.00968 -0.1345 0.5230 0.9999
6.750 1.3613 0.01718 0.01006 -0.1333 0.5149 0.9999
7.000 1.3882 0.01746 0.01029 -0.1331 0.5078 0.9999
7.250 1.4068 0.01771 0.01067 -0.1315 0.4985 0.9999
7.500 1.4296 0.01792 0.01083 -0.1305 0.4885 0.9999
7.750 1.4476 0.01810 0.01109 -0.1287 0.4774 0.9999
8.000 1.4661 0.01835 0.01139 -0.1270 0.4667 0.9999
8.250 1.4878 0.01860 0.01159 -0.1259 0.4569 0.9999
8.500 1.5025 0.01888 0.01201 -0.1236 0.4463 0.9999
8.750 1.5206 0.01917 0.01235 -0.1219 0.4363 0.9999
9.000 1.5355 0.01946 0.01268 -0.1196 0.4250 0.9999
9.250 1.5477 0.01979 0.01312 -0.1169 0.4128 0.9999
9.500 1.5582 0.02015 0.01353 -0.1139 0.4005 0.9999
9.750 1.5674 0.02059 0.01401 -0.1108 0.3871 0.9999
10.000 1.5754 0.02114 0.01459 -0.1076 0.3724 0.9999
10.250 1.5820 0.02180 0.01529 -0.1043 0.3557 0.9999
10.500 1.5874 0.02262 0.01613 -0.1011 0.3364 0.9999
10.750 1.5895 0.02370 0.01717 -0.0976 0.3141 0.9999
11.000 1.5894 0.02506 0.01846 -0.0941 0.2887 0.9999
11.250 1.5853 0.02680 0.02008 -0.0905 0.2606 0.9999
11.500 1.5779 0.02895 0.02209 -0.0868 0.2304 0.9999
11.750 1.5676 0.03153 0.02451 -0.0833 0.1991 0.9999
12.000 1.5549 0.03453 0.02734 -0.0801 0.1694 0.9999
12.250 1.5413 0.03785 0.03052 -0.0772 0.1446 0.9999
12.500 1.5291 0.04126 0.03382 -0.0748 0.1235 0.9999
12.750 1.5173 0.04486 0.03735 -0.0728 0.1084 0.9999
13.000 1.5075 0.04844 0.04092 -0.0712 0.0967 0.9999
13.250 1.4987 0.05208 0.04457 -0.0699 0.0877 0.9999
13.500 1.4876 0.05611 0.04856 -0.0689 0.0813 0.9999
13.750 1.4838 0.05943 0.05197 -0.0681 0.0747 0.9999
14.000 1.4729 0.06361 0.05612 -0.0673 0.0704 0.9999
14.250 1.4713 0.06682 0.05945 -0.0668 0.0656 0.9999
14.500 1.4653 0.07058 0.06321 -0.0663 0.0621 0.9999
14.750 1.4606 0.07412 0.06680 -0.0658 0.0589 0.9999
15.000 1.4597 0.07732 0.07009 -0.0655 0.0557 0.9999
15.250 1.4571 0.08070 0.07348 -0.0652 0.0531 0.9999
15.500 1.4559 0.08371 0.07651 -0.0645 0.0507 0.9999
15.750 1.4575 0.08666 0.07958 -0.0643 0.0483 0.9999
16.000 1.4584 0.08961 0.08257 -0.0642 0.0461 0.9999
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Polar data table (+)
Polar graphs
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