NACA 6412 (naca6412-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 6412 (naca6412-il) Reynolds number: 500,000 Max Cl/Cd: 114.15 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca6412-il-500000.txt Download as CSV file: xf-naca6412-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1344 0.08939 0.08696 -0.0883 0.9771 0.0354
-9.250 -0.2938 0.02885 0.02541 -0.1484 0.9457 0.0283
-9.000 -0.2807 0.02451 0.02046 -0.1502 0.9392 0.0288
-8.750 -0.2627 0.02239 0.01793 -0.1500 0.9319 0.0293
-8.500 -0.2407 0.02012 0.01534 -0.1503 0.9273 0.0300
-8.250 -0.2191 0.01921 0.01438 -0.1496 0.9208 0.0306
-8.000 -0.1937 0.01861 0.01370 -0.1494 0.9157 0.0314
-7.750 -0.1673 0.01780 0.01274 -0.1494 0.9115 0.0324
-7.500 -0.1435 0.01696 0.01172 -0.1489 0.9055 0.0332
-7.250 -0.1184 0.01622 0.01078 -0.1484 0.8996 0.0341
-7.000 -0.0929 0.01507 0.00944 -0.1482 0.8949 0.0349
-6.750 -0.0682 0.01447 0.00881 -0.1477 0.8886 0.0360
-6.500 -0.0419 0.01404 0.00832 -0.1474 0.8824 0.0373
-6.000 0.0114 0.01319 0.00723 -0.1467 0.8699 0.0400
-5.750 0.0372 0.01249 0.00649 -0.1464 0.8637 0.0418
-5.500 0.0643 0.01217 0.00613 -0.1461 0.8575 0.0437
-5.250 0.0908 0.01188 0.00574 -0.1457 0.8501 0.0458
-5.000 0.1179 0.01140 0.00521 -0.1455 0.8438 0.0486
-4.750 0.1441 0.01119 0.00498 -0.1450 0.8354 0.0516
-4.500 0.1714 0.01085 0.00454 -0.1448 0.8285 0.0549
-4.250 0.1976 0.01060 0.00430 -0.1444 0.8202 0.0586
-4.000 0.2254 0.01048 0.00408 -0.1441 0.8124 0.0622
-3.750 0.2513 0.01018 0.00380 -0.1437 0.8036 0.0676
-3.500 0.2790 0.01009 0.00361 -0.1435 0.7954 0.0720
-3.250 0.3050 0.00983 0.00338 -0.1430 0.7863 0.0784
-3.000 0.3323 0.00973 0.00320 -0.1427 0.7779 0.0845
-2.750 0.3586 0.00957 0.00306 -0.1423 0.7681 0.0925
-2.500 0.3853 0.00945 0.00290 -0.1420 0.7590 0.1011
-2.250 0.4119 0.00939 0.00281 -0.1416 0.7484 0.1099
-2.000 0.4382 0.00927 0.00270 -0.1411 0.7383 0.1218
-1.750 0.4645 0.00920 0.00260 -0.1407 0.7281 0.1339
-1.500 0.4907 0.00914 0.00254 -0.1403 0.7171 0.1468
-1.250 0.5169 0.00911 0.00248 -0.1398 0.7064 0.1609
-1.000 0.5429 0.00910 0.00245 -0.1393 0.6949 0.1772
-0.750 0.5688 0.00907 0.00244 -0.1389 0.6835 0.1956
-0.500 0.5946 0.00906 0.00243 -0.1384 0.6725 0.2155
-0.250 0.6201 0.00907 0.00244 -0.1378 0.6610 0.2375
0.000 0.6458 0.00907 0.00247 -0.1373 0.6494 0.2623
0.250 0.6712 0.00908 0.00250 -0.1368 0.6385 0.2907
0.500 0.6963 0.00908 0.00254 -0.1362 0.6275 0.3269
0.750 0.7212 0.00902 0.00259 -0.1356 0.6168 0.3775
1.000 0.7419 0.00864 0.00273 -0.1343 0.6072 0.5862
1.250 0.8011 0.00799 0.00289 -0.1414 0.5961 0.9999
1.500 0.8268 0.00814 0.00295 -0.1409 0.5870 0.9999
1.750 0.8523 0.00830 0.00302 -0.1404 0.5780 0.9999
2.000 0.8782 0.00845 0.00311 -0.1399 0.5698 0.9999
2.250 0.9038 0.00861 0.00320 -0.1395 0.5618 0.9999
2.500 0.9297 0.00878 0.00331 -0.1391 0.5548 0.9999
2.750 0.9556 0.00893 0.00341 -0.1387 0.5476 0.9999
3.000 0.9810 0.00914 0.00354 -0.1382 0.5410 0.9999
3.250 1.0072 0.00926 0.00366 -0.1379 0.5347 0.9999
3.500 1.0328 0.00943 0.00379 -0.1375 0.5283 0.9999
3.750 1.0584 0.00963 0.00395 -0.1371 0.5223 0.9999
4.000 1.0843 0.00977 0.00409 -0.1367 0.5163 0.9999
4.250 1.1098 0.00996 0.00424 -0.1363 0.5107 0.9999
4.500 1.1353 0.01016 0.00442 -0.1359 0.5051 0.9999
4.750 1.1609 0.01031 0.00459 -0.1355 0.4993 0.9999
5.000 1.1861 0.01051 0.00476 -0.1351 0.4938 0.9999
5.250 1.2116 0.01073 0.00497 -0.1347 0.4889 0.9999
5.500 1.2367 0.01088 0.00516 -0.1342 0.4832 0.9999
5.750 1.2611 0.01109 0.00535 -0.1337 0.4769 0.9999
6.000 1.2856 0.01131 0.00557 -0.1331 0.4708 0.9999
6.250 1.3093 0.01147 0.00576 -0.1324 0.4633 0.9999
6.500 1.3320 0.01172 0.00598 -0.1315 0.4550 0.9999
6.750 1.3544 0.01188 0.00617 -0.1305 0.4454 0.9999
7.000 1.3764 0.01212 0.00640 -0.1295 0.4364 0.9999
7.250 1.3985 0.01233 0.00663 -0.1286 0.4275 0.9999
7.500 1.4203 0.01257 0.00688 -0.1276 0.4189 0.9999
7.750 1.4404 0.01282 0.00715 -0.1262 0.4091 0.9999
8.000 1.4601 0.01307 0.00742 -0.1248 0.3982 0.9999
8.250 1.4785 0.01339 0.00773 -0.1232 0.3873 0.9999
8.500 1.4960 0.01377 0.00808 -0.1215 0.3748 0.9999
8.750 1.5139 0.01415 0.00847 -0.1199 0.3603 0.9999
9.000 1.5288 0.01467 0.00894 -0.1178 0.3423 0.9999
9.250 1.5427 0.01529 0.00949 -0.1157 0.3195 0.9999
9.500 1.5530 0.01612 0.01020 -0.1131 0.2945 0.9999
9.750 1.5615 0.01710 0.01105 -0.1104 0.2660 0.9999
10.000 1.5684 0.01824 0.01203 -0.1076 0.2367 0.9999
10.250 1.5732 0.01955 0.01318 -0.1046 0.2070 0.9999
10.500 1.5761 0.02103 0.01451 -0.1016 0.1774 0.9999
10.750 1.5778 0.02266 0.01600 -0.0986 0.1498 0.9999
11.000 1.5792 0.02439 0.01759 -0.0957 0.1260 0.9999
11.250 1.5797 0.02626 0.01935 -0.0930 0.1058 0.9999
11.500 1.5818 0.02808 0.02111 -0.0906 0.0897 0.9999
11.750 1.5841 0.02998 0.02296 -0.0884 0.0771 0.9999
12.000 1.5861 0.03196 0.02493 -0.0864 0.0673 0.9999
12.250 1.5874 0.03408 0.02705 -0.0845 0.0598 0.9999
12.500 1.5904 0.03615 0.02913 -0.0829 0.0537 0.9999
12.750 1.5928 0.03834 0.03136 -0.0814 0.0489 0.9999
13.000 1.5928 0.04082 0.03387 -0.0800 0.0449 0.9999
13.250 1.5952 0.04319 0.03631 -0.0788 0.0418 0.9999
13.500 1.5959 0.04581 0.03897 -0.0778 0.0390 0.9999
13.750 1.5928 0.04890 0.04212 -0.0767 0.0366 0.9999
14.000 1.5954 0.05145 0.04477 -0.0760 0.0345 0.9999
14.250 1.5936 0.05457 0.04794 -0.0753 0.0327 0.9999
14.500 1.5871 0.05833 0.05176 -0.0746 0.0311 0.9999
14.750 1.5890 0.06114 0.05468 -0.0742 0.0297 0.9999
15.000 1.5882 0.06432 0.05794 -0.0739 0.0283 0.9999
15.250 1.5833 0.06808 0.06176 -0.0737 0.0272 0.9999
15.500 1.5733 0.07257 0.06632 -0.0735 0.0263 0.9999
15.750 1.5732 0.07582 0.06969 -0.0735 0.0255 0.9999
16.000 1.5708 0.07938 0.07334 -0.0735 0.0247 0.9999
16.250 1.5677 0.08308 0.07712 -0.0736 0.0240 0.9999
16.500 1.5633 0.08699 0.08112 -0.0739 0.0233 0.9999
16.750 1.5568 0.09124 0.08543 -0.0743 0.0228 0.9999
|
Polar data table (+)
Polar graphs
<< Back to NACA 6412 (naca6412-il)