NACA 6412 (naca6412-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 6412 (naca6412-il) Reynolds number: 500,000 Max Cl/Cd: 111.27 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca6412-il-500000-n5.txt Download as CSV file: xf-naca6412-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.2797 0.14016 0.13762 -0.0518 0.9963 0.0133
-13.250 -0.2707 0.13608 0.13353 -0.0546 0.9952 0.0135
-11.750 -0.5565 0.03130 0.02774 -0.1409 0.9522 0.0181
-11.500 -0.5418 0.02803 0.02425 -0.1438 0.9458 0.0184
-11.250 -0.5201 0.02606 0.02212 -0.1455 0.9420 0.0187
-11.000 -0.5022 0.02456 0.02047 -0.1457 0.9354 0.0190
-10.750 -0.4807 0.02319 0.01893 -0.1462 0.9302 0.0193
-10.500 -0.4570 0.02195 0.01752 -0.1468 0.9263 0.0197
-10.250 -0.4363 0.02085 0.01626 -0.1465 0.9199 0.0200
-10.000 -0.4132 0.01980 0.01504 -0.1465 0.9146 0.0204
-9.750 -0.3885 0.01884 0.01389 -0.1466 0.9103 0.0208
-9.500 -0.3654 0.01804 0.01293 -0.1463 0.9039 0.0212
-9.250 -0.3411 0.01722 0.01196 -0.1461 0.8981 0.0216
-9.000 -0.3160 0.01653 0.01119 -0.1460 0.8921 0.0221
-8.750 -0.2913 0.01599 0.01055 -0.1456 0.8838 0.0227
-8.500 -0.2652 0.01548 0.00992 -0.1454 0.8763 0.0233
-8.250 -0.2400 0.01496 0.00930 -0.1451 0.8681 0.0239
-8.000 -0.2138 0.01446 0.00866 -0.1449 0.8620 0.0245
-7.750 -0.1878 0.01400 0.00809 -0.1446 0.8557 0.0250
-7.500 -0.1620 0.01351 0.00751 -0.1444 0.8487 0.0257
-7.250 -0.1355 0.01312 0.00706 -0.1442 0.8423 0.0265
-7.000 -0.1090 0.01279 0.00665 -0.1439 0.8350 0.0274
-6.750 -0.0821 0.01249 0.00625 -0.1437 0.8283 0.0285
-6.500 -0.0554 0.01220 0.00587 -0.1434 0.8209 0.0295
-6.250 -0.0290 0.01185 0.00546 -0.1432 0.8131 0.0306
-6.000 -0.0022 0.01159 0.00514 -0.1429 0.8054 0.0319
-5.750 0.0247 0.01135 0.00482 -0.1426 0.7972 0.0333
-5.500 0.0516 0.01111 0.00450 -0.1424 0.7898 0.0349
-5.250 0.0783 0.01090 0.00425 -0.1421 0.7812 0.0369
-5.000 0.1053 0.01073 0.00401 -0.1418 0.7727 0.0392
-4.750 0.1319 0.01054 0.00377 -0.1415 0.7633 0.0415
-4.500 0.1588 0.01039 0.00357 -0.1412 0.7544 0.0442
-4.250 0.1856 0.01027 0.00337 -0.1409 0.7452 0.0468
-4.000 0.2123 0.01012 0.00320 -0.1406 0.7355 0.0503
-3.750 0.2390 0.01005 0.00304 -0.1402 0.7256 0.0537
-3.500 0.2655 0.00992 0.00290 -0.1399 0.7151 0.0579
-3.250 0.2922 0.00985 0.00276 -0.1395 0.7054 0.0620
-3.000 0.3186 0.00977 0.00265 -0.1392 0.6952 0.0675
-2.750 0.3453 0.00971 0.00255 -0.1388 0.6852 0.0729
-2.500 0.3714 0.00965 0.00247 -0.1384 0.6748 0.0800
-2.250 0.3977 0.00961 0.00240 -0.1380 0.6634 0.0871
-2.000 0.4240 0.00959 0.00234 -0.1376 0.6526 0.0951
-1.750 0.4498 0.00957 0.00229 -0.1371 0.6420 0.1038
-1.500 0.4763 0.00956 0.00225 -0.1368 0.6315 0.1122
-1.250 0.5023 0.00956 0.00223 -0.1363 0.6211 0.1223
-1.000 0.5280 0.00957 0.00222 -0.1358 0.6102 0.1336
-0.750 0.5542 0.00957 0.00222 -0.1354 0.6002 0.1467
-0.500 0.5800 0.00961 0.00223 -0.1350 0.5910 0.1602
-0.250 0.6062 0.00962 0.00225 -0.1346 0.5815 0.1751
0.000 0.6318 0.00966 0.00228 -0.1341 0.5726 0.1909
0.250 0.6578 0.00969 0.00232 -0.1337 0.5633 0.2081
0.500 0.6835 0.00973 0.00237 -0.1333 0.5555 0.2285
0.750 0.7094 0.00976 0.00243 -0.1329 0.5473 0.2488
1.000 0.7349 0.00981 0.00250 -0.1324 0.5398 0.2713
1.250 0.7609 0.00983 0.00257 -0.1320 0.5324 0.2989
1.500 0.7860 0.00987 0.00265 -0.1315 0.5255 0.3318
1.750 0.8116 0.00985 0.00274 -0.1311 0.5191 0.3758
2.000 0.8325 0.00942 0.00293 -0.1299 0.5126 0.6235
2.500 0.9166 0.00906 0.00324 -0.1364 0.4998 0.9999
2.750 0.9422 0.00921 0.00335 -0.1359 0.4941 0.9999
3.000 0.9678 0.00937 0.00346 -0.1355 0.4890 0.9999
3.250 0.9940 0.00950 0.00358 -0.1352 0.4838 0.9999
3.500 1.0195 0.00966 0.00370 -0.1347 0.4784 0.9999
3.750 1.0445 0.00985 0.00385 -0.1342 0.4732 0.9999
4.000 1.0706 0.00998 0.00398 -0.1339 0.4682 0.9999
4.250 1.0961 0.01013 0.00413 -0.1335 0.4633 0.9999
4.500 1.1209 0.01033 0.00429 -0.1330 0.4583 0.9999
4.750 1.1463 0.01049 0.00446 -0.1325 0.4533 0.9999
5.000 1.1716 0.01065 0.00463 -0.1321 0.4480 0.9999
5.250 1.1964 0.01084 0.00481 -0.1316 0.4434 0.9999
5.500 1.2208 0.01104 0.00501 -0.1310 0.4386 0.9999
5.750 1.2458 0.01120 0.00519 -0.1306 0.4323 0.9999
6.000 1.2692 0.01142 0.00540 -0.1298 0.4253 0.9999
6.250 1.2930 0.01162 0.00562 -0.1292 0.4174 0.9999
6.500 1.3144 0.01191 0.00585 -0.1281 0.4067 0.9999
6.750 1.3362 0.01216 0.00609 -0.1270 0.3930 0.9999
7.000 1.3560 0.01247 0.00636 -0.1256 0.3783 0.9999
7.250 1.3750 0.01280 0.00666 -0.1241 0.3636 0.9999
7.500 1.3935 0.01318 0.00699 -0.1226 0.3484 0.9999
7.750 1.4110 0.01362 0.00737 -0.1209 0.3318 0.9999
8.000 1.4258 0.01420 0.00786 -0.1188 0.3101 0.9999
8.250 1.4409 0.01481 0.00838 -0.1168 0.2884 0.9999
8.500 1.4538 0.01556 0.00901 -0.1146 0.2650 0.9999
8.750 1.4663 0.01635 0.00969 -0.1124 0.2409 0.9999
9.000 1.4763 0.01731 0.01052 -0.1099 0.2145 0.9999
9.250 1.4839 0.01844 0.01149 -0.1071 0.1853 0.9999
9.500 1.4901 0.01970 0.01258 -0.1043 0.1571 0.9999
9.750 1.4955 0.02104 0.01378 -0.1016 0.1314 0.9999
10.000 1.5012 0.02241 0.01504 -0.0990 0.1089 0.9999
10.250 1.5074 0.02379 0.01634 -0.0966 0.0920 0.9999
10.500 1.5153 0.02510 0.01761 -0.0946 0.0799 0.9999
10.750 1.5232 0.02646 0.01894 -0.0927 0.0700 0.9999
11.000 1.5318 0.02780 0.02029 -0.0909 0.0624 0.9999
11.250 1.5405 0.02918 0.02169 -0.0893 0.0562 0.9999
11.500 1.5478 0.03072 0.02324 -0.0877 0.0506 0.9999
11.750 1.5553 0.03227 0.02481 -0.0862 0.0461 0.9999
12.000 1.5622 0.03393 0.02650 -0.0847 0.0425 0.9999
12.250 1.5689 0.03565 0.02827 -0.0834 0.0391 0.9999
12.500 1.5745 0.03753 0.03019 -0.0821 0.0362 0.9999
12.750 1.5802 0.03944 0.03216 -0.0809 0.0335 0.9999
13.000 1.5840 0.04161 0.03436 -0.0797 0.0312 0.9999
13.250 1.5899 0.04364 0.03646 -0.0788 0.0293 0.9999
13.500 1.5936 0.04594 0.03882 -0.0779 0.0275 0.9999
13.750 1.5962 0.04842 0.04136 -0.0771 0.0260 0.9999
14.000 1.5997 0.05083 0.04386 -0.0764 0.0247 0.9999
14.250 1.6017 0.05350 0.04659 -0.0757 0.0234 0.9999
14.500 1.6018 0.05642 0.04958 -0.0752 0.0222 0.9999
14.750 1.6035 0.05923 0.05247 -0.0747 0.0213 0.9999
15.000 1.6044 0.06215 0.05548 -0.0744 0.0203 0.9999
15.250 1.6040 0.06528 0.05869 -0.0741 0.0195 0.9999
15.500 1.6022 0.06864 0.06212 -0.0739 0.0187 0.9999
15.750 1.6006 0.07203 0.06559 -0.0738 0.0181 0.9999
16.000 1.5999 0.07534 0.06901 -0.0738 0.0175 0.9999
16.250 1.5982 0.07879 0.07255 -0.0738 0.0170 0.9999
16.500 1.5956 0.08240 0.07624 -0.0740 0.0165 0.9999
16.750 1.5923 0.08614 0.08008 -0.0742 0.0161 0.9999
17.000 1.5883 0.09004 0.08405 -0.0746 0.0157 0.9999
17.250 1.5833 0.09409 0.08818 -0.0750 0.0153 0.9999
|
Polar data table (+)
Polar graphs
<< Back to NACA 6412 (naca6412-il)