NACA 6412 (naca6412-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 6412 (naca6412-il) Reynolds number: 200,000 Max Cl/Cd: 81.22 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca6412-il-200000-n5.txt Download as CSV file: xf-naca6412-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2812 0.03450 0.02977 -0.1366 0.9274 0.0297
-8.500 -0.2655 0.03216 0.02722 -0.1374 0.9197 0.0301
-8.250 -0.2431 0.02984 0.02464 -0.1390 0.9143 0.0307
-8.000 -0.2168 0.02742 0.02186 -0.1410 0.9107 0.0316
-7.750 -0.1997 0.02552 0.01960 -0.1405 0.9021 0.0328
-7.500 -0.1743 0.02333 0.01688 -0.1414 0.8967 0.0342
-7.250 -0.1485 0.02220 0.01562 -0.1415 0.8907 0.0351
-7.000 -0.1241 0.02135 0.01466 -0.1412 0.8832 0.0359
-6.750 -0.0949 0.02038 0.01351 -0.1418 0.8786 0.0372
-6.500 -0.0709 0.01951 0.01242 -0.1413 0.8716 0.0387
-6.250 -0.0445 0.01866 0.01136 -0.1412 0.8655 0.0404
-6.000 -0.0144 0.01809 0.01075 -0.1417 0.8611 0.0421
-5.750 0.0094 0.01755 0.01011 -0.1410 0.8531 0.0439
-5.500 0.0378 0.01688 0.00922 -0.1410 0.8471 0.0461
-5.250 0.0648 0.01637 0.00869 -0.1409 0.8406 0.0482
-5.000 0.0914 0.01598 0.00823 -0.1406 0.8331 0.0512
-4.750 0.1210 0.01548 0.00759 -0.1409 0.8274 0.0545
-4.500 0.1461 0.01516 0.00725 -0.1403 0.8185 0.0576
-4.250 0.1752 0.01480 0.00676 -0.1404 0.8118 0.0619
-4.000 0.2010 0.01449 0.00645 -0.1400 0.8033 0.0659
-3.750 0.2294 0.01421 0.00607 -0.1399 0.7959 0.0711
-3.500 0.2558 0.01394 0.00580 -0.1396 0.7870 0.0763
-3.250 0.2840 0.01373 0.00547 -0.1395 0.7788 0.0828
-3.000 0.3102 0.01350 0.00526 -0.1391 0.7693 0.0895
-2.750 0.3383 0.01331 0.00498 -0.1389 0.7610 0.0972
-2.500 0.3644 0.01315 0.00482 -0.1385 0.7510 0.1055
-2.250 0.3918 0.01299 0.00461 -0.1383 0.7418 0.1142
-2.000 0.4183 0.01289 0.00445 -0.1379 0.7315 0.1250
-1.750 0.4450 0.01277 0.00434 -0.1376 0.7218 0.1375
-1.500 0.4718 0.01268 0.00423 -0.1372 0.7121 0.1505
-1.250 0.4981 0.01261 0.00415 -0.1368 0.7019 0.1645
-1.000 0.5247 0.01256 0.00406 -0.1365 0.6920 0.1802
-0.750 0.5507 0.01252 0.00402 -0.1360 0.6811 0.1977
-0.500 0.5768 0.01249 0.00399 -0.1356 0.6709 0.2171
-0.250 0.6029 0.01247 0.00397 -0.1352 0.6610 0.2386
0.000 0.6286 0.01246 0.00398 -0.1347 0.6507 0.2625
0.250 0.6544 0.01246 0.00398 -0.1343 0.6411 0.2892
0.500 0.6797 0.01244 0.00401 -0.1337 0.6309 0.3217
0.750 0.7050 0.01240 0.00405 -0.1332 0.6220 0.3646
1.000 0.7286 0.01217 0.00414 -0.1324 0.6129 0.4740
1.250 0.7775 0.01131 0.00427 -0.1368 0.6034 0.9999
1.500 0.8032 0.01148 0.00432 -0.1363 0.5947 0.9999
1.750 0.8289 0.01165 0.00440 -0.1359 0.5867 0.9999
2.000 0.8544 0.01184 0.00449 -0.1354 0.5785 0.9999
2.250 0.8800 0.01202 0.00460 -0.1349 0.5710 0.9999
2.500 0.9055 0.01221 0.00472 -0.1344 0.5634 0.9999
2.750 0.9311 0.01242 0.00484 -0.1340 0.5567 0.9999
3.000 0.9564 0.01261 0.00501 -0.1335 0.5494 0.9999
3.250 0.9817 0.01283 0.00515 -0.1330 0.5428 0.9999
3.500 1.0071 0.01304 0.00533 -0.1326 0.5364 0.9999
3.750 1.0322 0.01325 0.00552 -0.1321 0.5299 0.9999
4.250 1.0825 0.01370 0.00593 -0.1311 0.5181 0.9999
4.500 1.1073 0.01394 0.00615 -0.1306 0.5121 0.9999
4.750 1.1323 0.01420 0.00637 -0.1301 0.5066 0.9999
5.000 1.1567 0.01442 0.00664 -0.1296 0.5003 0.9999
5.250 1.1812 0.01467 0.00689 -0.1290 0.4946 0.9999
5.500 1.2058 0.01495 0.00715 -0.1285 0.4894 0.9999
5.750 1.2296 0.01519 0.00746 -0.1278 0.4830 0.9999
6.000 1.2533 0.01546 0.00773 -0.1271 0.4769 0.9999
6.250 1.2773 0.01575 0.00804 -0.1265 0.4716 0.9999
6.500 1.3003 0.01601 0.00838 -0.1258 0.4653 0.9999
6.750 1.3230 0.01631 0.00868 -0.1249 0.4587 0.9999
7.000 1.3449 0.01660 0.00904 -0.1239 0.4514 0.9999
7.250 1.3659 0.01690 0.00937 -0.1228 0.4433 0.9999
7.500 1.3851 0.01721 0.00972 -0.1213 0.4331 0.9999
7.750 1.4024 0.01755 0.01005 -0.1195 0.4213 0.9999
8.000 1.4175 0.01790 0.01043 -0.1173 0.4079 0.9999
8.250 1.4321 0.01827 0.01084 -0.1150 0.3945 0.9999
8.500 1.4467 0.01870 0.01129 -0.1129 0.3813 0.9999
8.750 1.4606 0.01919 0.01179 -0.1106 0.3677 0.9999
9.000 1.4733 0.01975 0.01236 -0.1083 0.3524 0.9999
9.250 1.4845 0.02041 0.01301 -0.1058 0.3350 0.9999
9.500 1.4932 0.02122 0.01378 -0.1031 0.3153 0.9999
9.750 1.4997 0.02221 0.01470 -0.1002 0.2937 0.9999
10.000 1.5048 0.02336 0.01578 -0.0973 0.2701 0.9999
10.250 1.5074 0.02474 0.01707 -0.0943 0.2458 0.9999
10.500 1.5080 0.02635 0.01856 -0.0912 0.2202 0.9999
10.750 1.5079 0.02812 0.02024 -0.0883 0.1952 0.9999
11.000 1.5060 0.03013 0.02214 -0.0855 0.1719 0.9999
11.250 1.5038 0.03228 0.02421 -0.0830 0.1499 0.9999
11.500 1.5006 0.03462 0.02647 -0.0805 0.1308 0.9999
11.750 1.4983 0.03700 0.02881 -0.0784 0.1139 0.9999
12.000 1.4958 0.03949 0.03128 -0.0765 0.0999 0.9999
12.250 1.4937 0.04207 0.03385 -0.0749 0.0885 0.9999
12.500 1.4914 0.04478 0.03656 -0.0734 0.0791 0.9999
12.750 1.4895 0.04755 0.03934 -0.0722 0.0712 0.9999
13.000 1.4887 0.05030 0.04214 -0.0711 0.0648 0.9999
13.250 1.4862 0.05332 0.04521 -0.0702 0.0597 0.9999
13.500 1.4861 0.05617 0.04815 -0.0695 0.0550 0.9999
13.750 1.4830 0.05943 0.05145 -0.0688 0.0513 0.9999
14.000 1.4826 0.06244 0.05456 -0.0684 0.0480 0.9999
14.250 1.4797 0.06582 0.05799 -0.0680 0.0452 0.9999
14.500 1.4769 0.06927 0.06153 -0.0677 0.0429 0.9999
14.750 1.4757 0.07256 0.06493 -0.0676 0.0407 0.9999
15.000 1.4725 0.07614 0.06860 -0.0675 0.0388 0.9999
15.250 1.4674 0.08004 0.07257 -0.0676 0.0372 0.9999
15.500 1.4655 0.08357 0.07621 -0.0677 0.0357 0.9999
15.750 1.4633 0.08717 0.07992 -0.0679 0.0342 0.9999
16.000 1.4600 0.09095 0.08378 -0.0682 0.0328 0.9999
16.250 1.4549 0.09500 0.08791 -0.0687 0.0317 0.9999
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