NACA 6412 (naca6412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 6412 (naca6412-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.61 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca6412-il-1000000-n5.txt Download as CSV file: xf-naca6412-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3133 0.14165 0.13978 -0.0534 0.9966 0.0099
-14.250 -0.3023 0.13860 0.13673 -0.0557 0.9958 0.0100
-13.250 -0.7265 0.02680 0.02365 -0.1446 0.9505 0.0142
-13.000 -0.7102 0.02449 0.02114 -0.1458 0.9447 0.0144
-12.750 -0.6912 0.02284 0.01932 -0.1464 0.9398 0.0145
-12.500 -0.6710 0.02151 0.01785 -0.1467 0.9342 0.0147
-12.250 -0.6492 0.02043 0.01662 -0.1467 0.9291 0.0148
-12.000 -0.6266 0.01946 0.01552 -0.1468 0.9245 0.0150
-11.750 -0.6051 0.01832 0.01426 -0.1468 0.9189 0.0153
-11.500 -0.5819 0.01745 0.01328 -0.1466 0.9135 0.0156
-11.250 -0.5575 0.01678 0.01251 -0.1465 0.9086 0.0159
-11.000 -0.5327 0.01619 0.01185 -0.1464 0.9031 0.0162
-10.750 -0.5076 0.01564 0.01121 -0.1462 0.8976 0.0165
-10.500 -0.4822 0.01512 0.01059 -0.1461 0.8924 0.0168
-10.250 -0.4568 0.01458 0.00996 -0.1459 0.8861 0.0171
-10.000 -0.4314 0.01411 0.00937 -0.1456 0.8787 0.0174
-9.750 -0.4056 0.01367 0.00883 -0.1454 0.8705 0.0177
-9.500 -0.3799 0.01329 0.00833 -0.1451 0.8613 0.0179
-9.250 -0.3540 0.01284 0.00779 -0.1449 0.8529 0.0182
-9.000 -0.3283 0.01238 0.00725 -0.1446 0.8454 0.0187
-8.750 -0.3019 0.01201 0.00681 -0.1444 0.8388 0.0191
-8.500 -0.2754 0.01170 0.00642 -0.1442 0.8313 0.0195
-8.250 -0.2487 0.01141 0.00607 -0.1440 0.8246 0.0200
-8.000 -0.2217 0.01115 0.00574 -0.1438 0.8173 0.0206
-7.750 -0.1950 0.01090 0.00540 -0.1435 0.8101 0.0210
-7.500 -0.1679 0.01066 0.00509 -0.1433 0.8023 0.0214
-7.250 -0.1416 0.01037 0.00473 -0.1430 0.7939 0.0222
-7.000 -0.1146 0.01012 0.00443 -0.1428 0.7860 0.0228
-6.750 -0.0877 0.00993 0.00418 -0.1426 0.7781 0.0236
-6.500 -0.0604 0.00974 0.00393 -0.1424 0.7705 0.0244
-6.250 -0.0335 0.00959 0.00371 -0.1421 0.7616 0.0252
-6.000 -0.0065 0.00939 0.00347 -0.1419 0.7525 0.0265
-5.750 0.0202 0.00925 0.00328 -0.1416 0.7433 0.0277
-5.500 0.0475 0.00912 0.00309 -0.1414 0.7340 0.0290
-5.250 0.0743 0.00899 0.00291 -0.1411 0.7246 0.0305
-5.000 0.1012 0.00888 0.00275 -0.1408 0.7142 0.0324
-4.750 0.1282 0.00880 0.00261 -0.1405 0.7041 0.0341
-4.250 0.1820 0.00861 0.00235 -0.1399 0.6840 0.0391
-4.000 0.2088 0.00854 0.00223 -0.1396 0.6742 0.0417
-3.750 0.2357 0.00847 0.00214 -0.1393 0.6638 0.0446
-3.500 0.2625 0.00843 0.00204 -0.1390 0.6533 0.0474
-3.250 0.2890 0.00839 0.00197 -0.1387 0.6421 0.0511
-3.000 0.3159 0.00836 0.00189 -0.1384 0.6307 0.0548
-2.750 0.3425 0.00832 0.00183 -0.1380 0.6204 0.0595
-2.500 0.3690 0.00831 0.00178 -0.1377 0.6099 0.0637
-2.250 0.3958 0.00828 0.00174 -0.1374 0.5996 0.0699
-2.000 0.4222 0.00828 0.00171 -0.1370 0.5888 0.0768
-1.500 0.4754 0.00826 0.00166 -0.1364 0.5697 0.0927
-1.250 0.5019 0.00828 0.00165 -0.1360 0.5602 0.1001
-1.000 0.5286 0.00828 0.00165 -0.1358 0.5515 0.1084
-0.750 0.5549 0.00831 0.00166 -0.1354 0.5423 0.1176
-0.500 0.5817 0.00832 0.00167 -0.1351 0.5347 0.1270
-0.250 0.6081 0.00834 0.00169 -0.1348 0.5268 0.1386
0.000 0.6347 0.00836 0.00172 -0.1345 0.5198 0.1513
0.250 0.6612 0.00838 0.00175 -0.1342 0.5125 0.1663
0.500 0.6874 0.00842 0.00179 -0.1338 0.5062 0.1809
0.750 0.7142 0.00843 0.00184 -0.1336 0.5004 0.1966
1.000 0.7403 0.00847 0.00189 -0.1332 0.4938 0.2159
1.250 0.7667 0.00851 0.00195 -0.1329 0.4883 0.2334
1.500 0.7932 0.00853 0.00201 -0.1326 0.4829 0.2532
1.750 0.8194 0.00857 0.00209 -0.1323 0.4777 0.2761
2.000 0.8453 0.00861 0.00217 -0.1319 0.4729 0.3031
2.250 0.8717 0.00862 0.00225 -0.1316 0.4685 0.3319
2.500 0.8977 0.00863 0.00234 -0.1313 0.4637 0.3687
2.750 0.9190 0.00822 0.00254 -0.1302 0.4590 0.6379
3.000 0.9909 0.00776 0.00282 -0.1405 0.4530 0.9999
3.250 1.0178 0.00787 0.00291 -0.1403 0.4486 0.9999
3.500 1.0442 0.00800 0.00301 -0.1400 0.4439 0.9999
3.750 1.0703 0.00814 0.00313 -0.1397 0.4390 0.9999
4.000 1.0973 0.00825 0.00323 -0.1396 0.4344 0.9999
4.250 1.1238 0.00837 0.00334 -0.1394 0.4301 0.9999
4.500 1.1499 0.00852 0.00347 -0.1391 0.4257 0.9999
4.750 1.1760 0.00866 0.00360 -0.1389 0.4208 0.9999
5.000 1.2022 0.00880 0.00373 -0.1386 0.4142 0.9999
5.250 1.2271 0.00900 0.00390 -0.1381 0.4066 0.9999
5.500 1.2526 0.00917 0.00405 -0.1378 0.3960 0.9999
5.750 1.2768 0.00941 0.00423 -0.1372 0.3832 0.9999
6.000 1.3004 0.00967 0.00444 -0.1365 0.3690 0.9999
6.250 1.3228 0.01001 0.00468 -0.1357 0.3497 0.9999
6.500 1.3451 0.01034 0.00493 -0.1348 0.3327 0.9999
6.750 1.3660 0.01075 0.00524 -0.1337 0.3133 0.9999
7.000 1.3848 0.01128 0.00563 -0.1322 0.2865 0.9999
7.250 1.4025 0.01181 0.00604 -0.1305 0.2641 0.9999
7.500 1.4173 0.01244 0.00651 -0.1284 0.2361 0.9999
7.750 1.4314 0.01312 0.00705 -0.1261 0.2085 0.9999
8.000 1.4447 0.01387 0.00764 -0.1238 0.1813 0.9999
8.250 1.4575 0.01464 0.00828 -0.1215 0.1568 0.9999
8.500 1.4687 0.01553 0.00901 -0.1190 0.1310 0.9999
8.750 1.4813 0.01634 0.00972 -0.1168 0.1108 0.9999
9.000 1.4924 0.01725 0.01052 -0.1145 0.0917 0.9999
9.250 1.5057 0.01805 0.01126 -0.1125 0.0788 0.9999
9.500 1.5189 0.01887 0.01203 -0.1106 0.0686 0.9999
9.750 1.5321 0.01971 0.01284 -0.1088 0.0603 0.9999
10.000 1.5459 0.02052 0.01364 -0.1071 0.0534 0.9999
10.250 1.5590 0.02140 0.01451 -0.1054 0.0477 0.9999
10.500 1.5716 0.02233 0.01543 -0.1038 0.0430 0.9999
10.750 1.5841 0.02328 0.01639 -0.1021 0.0388 0.9999
11.000 1.5963 0.02428 0.01741 -0.1005 0.0355 0.9999
11.250 1.6075 0.02538 0.01851 -0.0989 0.0322 0.9999
11.500 1.6192 0.02646 0.01962 -0.0974 0.0298 0.9999
11.750 1.6294 0.02768 0.02086 -0.0959 0.0273 0.9999
12.000 1.6398 0.02893 0.02214 -0.0944 0.0255 0.9999
12.250 1.6492 0.03028 0.02352 -0.0930 0.0235 0.9999
12.500 1.6573 0.03177 0.02504 -0.0915 0.0219 0.9999
12.750 1.6661 0.03324 0.02655 -0.0902 0.0205 0.9999
13.000 1.6733 0.03488 0.02824 -0.0889 0.0191 0.9999
13.250 1.6802 0.03662 0.03002 -0.0876 0.0181 0.9999
13.500 1.6874 0.03836 0.03181 -0.0865 0.0172 0.9999
13.750 1.6930 0.04029 0.03379 -0.0853 0.0163 0.9999
14.000 1.6974 0.04241 0.03596 -0.0842 0.0155 0.9999
14.250 1.7021 0.04456 0.03818 -0.0833 0.0148 0.9999
14.500 1.7069 0.04675 0.04043 -0.0824 0.0143 0.9999
14.750 1.7106 0.04908 0.04283 -0.0816 0.0138 0.9999
15.000 1.7131 0.05158 0.04539 -0.0809 0.0132 0.9999
15.250 1.7144 0.05429 0.04816 -0.0802 0.0127 0.9999
15.500 1.7146 0.05717 0.05111 -0.0796 0.0123 0.9999
15.750 1.7164 0.05992 0.05394 -0.0792 0.0120 0.9999
16.000 1.7170 0.06283 0.05693 -0.0788 0.0117 0.9999
16.250 1.7168 0.06587 0.06005 -0.0784 0.0114 0.9999
16.500 1.7159 0.06906 0.06331 -0.0782 0.0111 0.9999
16.750 1.7145 0.07235 0.06667 -0.0780 0.0109 0.9999
17.000 1.7122 0.07578 0.07017 -0.0780 0.0106 0.9999
17.250 1.7091 0.07931 0.07378 -0.0780 0.0103 0.9999
17.500 1.7048 0.08306 0.07761 -0.0780 0.0101 0.9999
17.750 1.6996 0.08699 0.08162 -0.0782 0.0099 0.9999
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