NACA 16-012 (naca16012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16-012 (naca16012-il) Reynolds number: 1,000,000 Max Cl/Cd: 55.75 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16012-il-1000000-n5.txt Download as CSV file: xf-naca16012-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-012
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
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0477 0.06372 0.06124 -0.0644 1.0000 0.0029
-16.250 -1.0754 0.05635 0.05368 -0.0676 1.0000 0.0029
-16.000 -1.0972 0.05104 0.04820 -0.0684 1.0000 0.0029
-15.750 -1.1135 0.04710 0.04410 -0.0677 1.0000 0.0029
-15.500 -1.1270 0.04391 0.04077 -0.0661 1.0000 0.0029
-15.250 -1.1381 0.04125 0.03796 -0.0638 1.0000 0.0029
-15.000 -1.1480 0.03895 0.03551 -0.0610 1.0000 0.0029
-14.750 -1.1551 0.03708 0.03352 -0.0579 1.0000 0.0030
-14.500 -1.1626 0.03537 0.03167 -0.0542 1.0000 0.0030
-14.250 -1.1677 0.03396 0.03015 -0.0504 1.0000 0.0030
-14.000 -1.1713 0.03226 0.02830 -0.0471 0.9997 0.0030
-13.750 -1.1696 0.03011 0.02595 -0.0451 0.9986 0.0032
-13.500 -1.1620 0.02848 0.02417 -0.0435 0.9976 0.0033
-13.250 -1.1503 0.02713 0.02269 -0.0423 0.9965 0.0033
-13.000 -1.1357 0.02596 0.02140 -0.0414 0.9957 0.0034
-12.750 -1.1194 0.02489 0.02022 -0.0406 0.9949 0.0035
-12.500 -1.1038 0.02391 0.01913 -0.0395 0.9938 0.0036
-12.250 -1.0875 0.02302 0.01814 -0.0384 0.9922 0.0037
-12.000 -1.0695 0.02215 0.01715 -0.0376 0.9908 0.0039
-11.750 -1.0498 0.02132 0.01621 -0.0370 0.9896 0.0040
-11.500 -1.0291 0.02052 0.01531 -0.0366 0.9885 0.0041
-11.250 -1.0073 0.01975 0.01445 -0.0364 0.9877 0.0043
-11.000 -0.9843 0.01903 0.01362 -0.0363 0.9870 0.0044
-10.750 -0.9601 0.01836 0.01287 -0.0364 0.9863 0.0046
-10.500 -0.9364 0.01769 0.01212 -0.0364 0.9855 0.0047
-10.250 -0.9191 0.01697 0.01131 -0.0349 0.9828 0.0050
-10.000 -0.8970 0.01638 0.01065 -0.0344 0.9811 0.0053
-9.750 -0.8732 0.01587 0.01009 -0.0343 0.9796 0.0056
-9.500 -0.8485 0.01538 0.00955 -0.0343 0.9783 0.0060
-9.250 -0.8233 0.01492 0.00904 -0.0343 0.9772 0.0064
-9.000 -0.7981 0.01448 0.00854 -0.0344 0.9762 0.0067
-8.750 -0.7779 0.01404 0.00805 -0.0332 0.9736 0.0071
-8.500 -0.7573 0.01359 0.00756 -0.0321 0.9708 0.0079
-8.250 -0.7341 0.01319 0.00714 -0.0316 0.9687 0.0086
-8.000 -0.7101 0.01283 0.00672 -0.0313 0.9670 0.0093
-7.750 -0.6855 0.01249 0.00633 -0.0310 0.9654 0.0100
-7.500 -0.6625 0.01212 0.00597 -0.0304 0.9635 0.0120
-7.250 -0.6426 0.01185 0.00571 -0.0291 0.9603 0.0138
-7.000 -0.6204 0.01158 0.00543 -0.0282 0.9576 0.0161
-6.750 -0.5969 0.01132 0.00519 -0.0276 0.9553 0.0195
-6.500 -0.5721 0.01111 0.00495 -0.0273 0.9534 0.0217
-6.250 -0.5461 0.01093 0.00474 -0.0273 0.9518 0.0228
-6.000 -0.5235 0.01070 0.00449 -0.0264 0.9492 0.0245
-5.750 -0.5010 0.01047 0.00425 -0.0255 0.9462 0.0267
-5.500 -0.4772 0.01026 0.00404 -0.0250 0.9436 0.0288
-5.250 -0.4526 0.01007 0.00383 -0.0246 0.9413 0.0305
-5.000 -0.4268 0.00989 0.00362 -0.0244 0.9393 0.0319
-4.750 -0.4008 0.00970 0.00341 -0.0243 0.9374 0.0343
-4.500 -0.3780 0.00951 0.00323 -0.0235 0.9345 0.0385
-4.250 -0.3542 0.00934 0.00307 -0.0228 0.9315 0.0417
-4.000 -0.3299 0.00916 0.00291 -0.0223 0.9288 0.0494
-3.750 -0.3057 0.00892 0.00274 -0.0218 0.9263 0.0677
-3.500 -0.2809 0.00866 0.00256 -0.0214 0.9241 0.0915
-3.250 -0.2575 0.00841 0.00242 -0.0208 0.9214 0.1212
-3.000 -0.2358 0.00815 0.00229 -0.0197 0.9180 0.1585
-2.750 -0.2143 0.00784 0.00215 -0.0187 0.9147 0.2071
-2.500 -0.1951 0.00735 0.00197 -0.0172 0.9115 0.2918
-2.250 -0.1754 0.00687 0.00179 -0.0158 0.9087 0.3792
-2.000 -0.1581 0.00648 0.00167 -0.0138 0.9049 0.4538
-1.750 -0.1426 0.00603 0.00153 -0.0113 0.9007 0.5385
-1.500 -0.1343 0.00538 0.00134 -0.0072 0.8964 0.6634
-1.250 -0.1245 0.00493 0.00128 -0.0031 0.8922 0.7639
-1.000 -0.1072 0.00476 0.00136 -0.0006 0.8881 0.8279
-0.750 -0.0828 0.00475 0.00141 0.0002 0.8848 0.8534
-0.500 -0.0549 0.00475 0.00143 0.0001 0.8820 0.8641
-0.250 -0.0264 0.00475 0.00144 -0.0002 0.8792 0.8701
0.000 0.0000 0.00476 0.00147 0.0000 0.8751 0.8751
0.250 0.0264 0.00475 0.00144 0.0002 0.8700 0.8792
0.500 0.0549 0.00475 0.00143 -0.0001 0.8641 0.8820
0.750 0.0829 0.00475 0.00141 -0.0002 0.8534 0.8848
1.000 0.1071 0.00476 0.00136 0.0006 0.8271 0.8881
1.250 0.1246 0.00493 0.00128 0.0031 0.7639 0.8923
1.500 0.1344 0.00538 0.00134 0.0072 0.6635 0.8964
1.750 0.1427 0.00603 0.00153 0.0113 0.5391 0.9007
2.000 0.1583 0.00648 0.00167 0.0137 0.4548 0.9049
2.250 0.1755 0.00687 0.00179 0.0157 0.3796 0.9087
2.500 0.1950 0.00736 0.00197 0.0172 0.2911 0.9115
2.750 0.2143 0.00784 0.00215 0.0186 0.2070 0.9147
3.000 0.2359 0.00815 0.00229 0.0197 0.1585 0.9180
3.250 0.2576 0.00841 0.00242 0.0207 0.1209 0.9214
3.500 0.2810 0.00866 0.00256 0.0214 0.0917 0.9240
3.750 0.3058 0.00892 0.00274 0.0218 0.0675 0.9263
4.000 0.3301 0.00915 0.00291 0.0223 0.0495 0.9287
4.250 0.3543 0.00934 0.00307 0.0228 0.0417 0.9315
4.500 0.3781 0.00951 0.00323 0.0234 0.0385 0.9345
4.750 0.4010 0.00970 0.00341 0.0242 0.0343 0.9374
5.000 0.4270 0.00989 0.00362 0.0244 0.0319 0.9392
5.250 0.4528 0.01007 0.00383 0.0245 0.0305 0.9413
5.500 0.4775 0.01026 0.00404 0.0249 0.0287 0.9435
5.750 0.5013 0.01047 0.00425 0.0255 0.0266 0.9461
6.000 0.5238 0.01070 0.00449 0.0263 0.0245 0.9492
6.250 0.5463 0.01093 0.00474 0.0272 0.0228 0.9518
6.500 0.5724 0.01111 0.00495 0.0272 0.0217 0.9534
6.750 0.5972 0.01133 0.00519 0.0275 0.0195 0.9553
7.000 0.6207 0.01158 0.00543 0.0281 0.0161 0.9576
7.250 0.6429 0.01185 0.00571 0.0290 0.0139 0.9602
7.500 0.6629 0.01212 0.00597 0.0303 0.0119 0.9634
7.750 0.6859 0.01249 0.00633 0.0309 0.0100 0.9654
8.000 0.7105 0.01282 0.00672 0.0312 0.0094 0.9670
8.250 0.7345 0.01319 0.00713 0.0315 0.0086 0.9687
8.500 0.7576 0.01359 0.00756 0.0321 0.0079 0.9708
8.750 0.7784 0.01403 0.00804 0.0331 0.0072 0.9736
9.000 0.7985 0.01448 0.00854 0.0343 0.0068 0.9762
9.250 0.8238 0.01492 0.00904 0.0342 0.0064 0.9772
9.500 0.8489 0.01538 0.00955 0.0342 0.0060 0.9783
9.750 0.8736 0.01587 0.01009 0.0342 0.0056 0.9796
10.000 0.8975 0.01638 0.01064 0.0343 0.0053 0.9811
10.250 0.9196 0.01697 0.01131 0.0348 0.0050 0.9828
10.500 0.9367 0.01769 0.01211 0.0363 0.0047 0.9856
10.750 0.9609 0.01835 0.01286 0.0363 0.0046 0.9864
11.000 0.9850 0.01903 0.01363 0.0361 0.0044 0.9870
11.250 1.0081 0.01974 0.01444 0.0362 0.0043 0.9877
11.500 1.0299 0.02051 0.01530 0.0365 0.0041 0.9886
11.750 1.0505 0.02131 0.01621 0.0369 0.0040 0.9896
12.000 1.0701 0.02216 0.01716 0.0375 0.0039 0.9909
12.250 1.0883 0.02302 0.01814 0.0382 0.0037 0.9923
12.500 1.1044 0.02393 0.01915 0.0394 0.0036 0.9939
12.750 1.1204 0.02490 0.02023 0.0404 0.0035 0.9950
13.000 1.1367 0.02597 0.02142 0.0412 0.0034 0.9957
13.250 1.1515 0.02713 0.02270 0.0420 0.0033 0.9966
13.500 1.1632 0.02849 0.02418 0.0432 0.0032 0.9976
13.750 1.1708 0.03012 0.02596 0.0448 0.0031 0.9987
14.000 1.1725 0.03227 0.02831 0.0469 0.0030 0.9997
14.250 1.1692 0.03386 0.03004 0.0503 0.0030 1.0000
14.500 1.1629 0.03534 0.03165 0.0542 0.0030 1.0000
14.750 1.1568 0.03696 0.03339 0.0577 0.0029 1.0000
15.000 1.1483 0.03895 0.03551 0.0610 0.0029 1.0000
15.250 1.1398 0.04114 0.03785 0.0637 0.0029 1.0000
15.500 1.1288 0.04380 0.04065 0.0659 0.0029 1.0000
15.750 1.1147 0.04706 0.04407 0.0676 0.0029 1.0000
16.000 1.0984 0.05103 0.04819 0.0682 0.0029 1.0000
16.250 1.0776 0.05623 0.05356 0.0674 0.0029 1.0000
16.500 1.0482 0.06393 0.06146 0.0640 0.0029 1.0000
16.750 0.9318 0.09520 0.09317 0.0454 0.0030 1.0000
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Polar data table (+)
Polar graphs
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