NACA 6412 (naca6412-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 6412 (naca6412-il) Reynolds number: 100,000 Max Cl/Cd: 53.09 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca6412-il-100000.txt Download as CSV file: xf-naca6412-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3657 0.12392 0.11950 -0.0276 1.0001 0.0956
-8.500 -0.3935 0.12437 0.12006 -0.0262 1.0001 0.0959
-8.250 -0.4195 0.12441 0.12020 -0.0243 1.0001 0.0960
-8.000 -0.3673 0.11524 0.11096 -0.0217 1.0001 0.0988
-7.750 -0.3473 0.11172 0.10742 -0.0242 0.9963 0.1026
-7.500 -0.3363 0.10865 0.10434 -0.0297 0.9895 0.1073
-7.250 -0.3428 0.10667 0.10238 -0.0508 0.9733 0.1103
-7.000 -0.3193 0.10099 0.09670 -0.0429 0.9727 0.1119
-6.750 -0.2956 0.09735 0.09303 -0.0429 0.9671 0.1149
-6.500 -0.2745 0.09372 0.08938 -0.0477 0.9594 0.1196
-6.250 -0.2591 0.08857 0.08416 -0.0661 0.9449 0.1262
-6.000 -0.2341 0.08517 0.08077 -0.0613 0.9427 0.1294
-5.750 -0.2208 0.08254 0.07814 -0.0622 0.9326 0.1341
-5.500 -0.1927 0.07702 0.07247 -0.0771 0.9225 0.1430
-5.250 -0.1747 0.07417 0.06965 -0.0752 0.9153 0.1457
-5.000 -0.1367 0.06949 0.06468 -0.0893 0.9061 0.1591
-4.750 -0.1209 0.06662 0.06191 -0.0860 0.8991 0.1619
-4.500 -0.0749 0.06220 0.05725 -0.0959 0.8945 0.1775
-4.250 -0.0320 0.04616 0.04005 -0.1114 0.8854 0.1116
-4.000 0.0124 0.04081 0.03396 -0.1169 0.8809 0.1094
-3.750 0.0596 0.03638 0.02884 -0.1219 0.8781 0.1111
-3.500 0.0792 0.03587 0.02850 -0.1209 0.8669 0.1160
-3.250 0.1250 0.03333 0.02534 -0.1243 0.8631 0.1230
-3.000 0.1528 0.03210 0.02391 -0.1247 0.8542 0.1299
-2.750 0.1925 0.03088 0.02234 -0.1265 0.8483 0.1399
-2.500 0.2394 0.02948 0.02085 -0.1297 0.8454 0.1523
-2.250 0.2610 0.02893 0.02013 -0.1286 0.8340 0.1619
-2.000 0.3063 0.02778 0.01881 -0.1312 0.8304 0.1776
-1.750 0.3528 0.02665 0.01766 -0.1340 0.8279 0.1973
-1.500 0.3729 0.02648 0.01742 -0.1325 0.8158 0.2126
-1.250 0.4158 0.02542 0.01645 -0.1346 0.8125 0.2365
-0.750 0.4773 0.02438 0.01548 -0.1349 0.7972 0.2886
-0.500 0.5058 0.02399 0.01516 -0.1348 0.7887 0.3210
-0.250 0.5387 0.02324 0.01457 -0.1352 0.7819 0.3636
0.000 0.5812 0.02202 0.01367 -0.1371 0.7785 0.4425
0.250 0.6154 0.02073 0.01371 -0.1380 0.7684 0.9999
0.500 0.6546 0.02038 0.01303 -0.1393 0.7631 0.9999
0.750 0.6783 0.02066 0.01315 -0.1384 0.7530 0.9999
1.000 0.7136 0.02045 0.01275 -0.1393 0.7469 0.9999
1.250 0.7388 0.02072 0.01290 -0.1387 0.7379 0.9999
1.500 0.7706 0.02067 0.01271 -0.1390 0.7307 0.9999
1.750 0.7990 0.02082 0.01276 -0.1389 0.7231 0.9999
2.000 0.8256 0.02103 0.01289 -0.1386 0.7148 0.9999
2.250 0.8638 0.02079 0.01251 -0.1399 0.7100 0.9999
2.500 0.8791 0.02152 0.01324 -0.1379 0.6992 0.9999
2.750 0.9159 0.02135 0.01295 -0.1391 0.6941 0.9999
3.000 0.9315 0.02212 0.01374 -0.1373 0.6841 0.9999
3.250 0.9656 0.02206 0.01360 -0.1380 0.6785 0.9999
3.500 0.9844 0.02274 0.01429 -0.1366 0.6698 0.9999
3.750 1.0139 0.02290 0.01441 -0.1368 0.6632 0.9999
4.000 1.0411 0.02323 0.01473 -0.1366 0.6567 0.9999
4.250 1.0612 0.02383 0.01537 -0.1354 0.6485 0.9999
4.500 1.0972 0.02376 0.01522 -0.1365 0.6435 0.9999
4.750 1.1094 0.02477 0.01633 -0.1343 0.6343 0.9999
5.000 1.1412 0.02486 0.01640 -0.1347 0.6284 0.9999
5.250 1.1609 0.02556 0.01716 -0.1335 0.6207 0.9999
5.500 1.1851 0.02599 0.01763 -0.1329 0.6135 0.9999
5.750 1.2210 0.02597 0.01758 -0.1339 0.6084 0.9999
6.000 1.2294 0.02715 0.01891 -0.1312 0.5990 0.9999
6.250 1.2657 0.02702 0.01875 -0.1322 0.5933 0.9999
6.500 1.2761 0.02814 0.02003 -0.1298 0.5843 0.9999
6.750 1.3072 0.02824 0.02015 -0.1300 0.5778 0.9999
7.000 1.3248 0.02905 0.02106 -0.1286 0.5699 0.9999
7.250 1.3505 0.02931 0.02139 -0.1281 0.5619 0.9999
7.500 1.3734 0.02977 0.02193 -0.1272 0.5538 0.9999
7.750 1.3974 0.03004 0.02227 -0.1264 0.5450 0.9999
8.000 1.4185 0.03047 0.02281 -0.1252 0.5360 0.9999
8.250 1.4526 0.03004 0.02236 -0.1255 0.5261 0.9999
8.500 1.4655 0.03050 0.02295 -0.1229 0.5140 0.9999
8.750 1.4912 0.03022 0.02269 -0.1219 0.5017 0.9999
9.000 1.5229 0.02963 0.02206 -0.1218 0.4889 0.9999
9.250 1.5396 0.02970 0.02221 -0.1196 0.4759 0.9999
9.500 1.5510 0.03002 0.02266 -0.1167 0.4630 0.9999
9.750 1.5674 0.03010 0.02281 -0.1145 0.4500 0.9999
10.000 1.5843 0.03007 0.02282 -0.1124 0.4364 0.9999
10.250 1.5975 0.03009 0.02288 -0.1096 0.4221 0.9999
10.500 1.6004 0.03041 0.02329 -0.1054 0.4076 0.9999
10.750 1.5968 0.03101 0.02403 -0.1004 0.3930 0.9999
11.000 1.5938 0.03171 0.02481 -0.0958 0.3771 0.9999
11.250 1.5904 0.03256 0.02571 -0.0915 0.3596 0.9999
11.500 1.5830 0.03388 0.02710 -0.0871 0.3399 0.9999
11.750 1.5733 0.03561 0.02886 -0.0830 0.3174 0.9999
12.000 1.5616 0.03775 0.03093 -0.0791 0.2920 0.9999
12.250 1.5460 0.04053 0.03358 -0.0755 0.2642 0.9999
12.500 1.5269 0.04401 0.03690 -0.0722 0.2352 0.9999
12.750 1.5063 0.04801 0.04073 -0.0695 0.2077 0.9999
13.000 1.4863 0.05230 0.04483 -0.0672 0.1842 0.9999
13.250 1.4684 0.05667 0.04902 -0.0654 0.1644 0.9999
13.500 1.4540 0.06082 0.05300 -0.0639 0.1482 0.9999
13.750 1.4437 0.06465 0.05671 -0.0626 0.1343 0.9999
14.000 1.4378 0.06807 0.06005 -0.0615 0.1222 0.9999
14.250 1.4357 0.07102 0.06294 -0.0602 0.1120 0.9999
14.500 1.4371 0.07351 0.06529 -0.0589 0.1031 0.9999
14.750 1.4389 0.07617 0.06797 -0.0580 0.0957 0.9999
15.000 1.4454 0.07823 0.07001 -0.0566 0.0890 0.9999
15.250 1.4517 0.08032 0.07205 -0.0556 0.0832 0.9999
15.500 1.4618 0.08210 0.07389 -0.0542 0.0782 0.9999
15.750 1.4668 0.08457 0.07647 -0.0535 0.0741 0.9999
16.000 1.4892 0.08512 0.07685 -0.0516 0.0696 0.9999
16.250 1.4906 0.08829 0.08031 -0.0511 0.0674 0.9999
16.500 1.4942 0.09122 0.08346 -0.0506 0.0651 0.9999
16.750 1.5004 0.09378 0.08613 -0.0501 0.0629 0.9999
17.000 1.5222 0.09526 0.08752 -0.0487 0.0601 0.9999
17.250 1.5087 0.10002 0.09261 -0.0492 0.0594 0.9999
17.500 1.4948 0.10510 0.09801 -0.0501 0.0587 0.9999
17.750 1.4799 0.11053 0.10375 -0.0514 0.0581 0.9999
18.000 1.4634 0.11645 0.10996 -0.0533 0.0577 0.9999
18.250 1.4440 0.12303 0.11683 -0.0558 0.0575 0.9999
18.500 1.4210 0.13053 0.12462 -0.0593 0.0575 0.9999
18.750 1.3943 0.13916 0.13353 -0.0639 0.0578 0.9999
|
Polar data table (+)
Polar graphs
<< Back to NACA 6412 (naca6412-il)