NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M19 AIRFOIL (m19-il) Reynolds number: 200,000 Max Cl/Cd: 77.39 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m19-il-200000.txt Download as CSV file: xf-m19-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M19 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2723 0.09572 0.09275 -0.0055 0.8434 0.0214
-8.000 -0.2682 0.09253 0.08952 -0.0058 0.8320 0.0219
-7.750 -0.3600 0.10342 0.10047 -0.0015 0.8653 0.0206
-7.500 -0.3536 0.09932 0.09628 -0.0005 0.8511 0.0210
-7.250 -0.3472 0.09613 0.09303 -0.0011 0.8380 0.0215
-7.000 -0.3384 0.09308 0.08991 -0.0026 0.8265 0.0222
-6.750 -0.3269 0.08999 0.08676 -0.0050 0.8153 0.0232
-6.500 -0.3135 0.08681 0.08353 -0.0079 0.8050 0.0241
-6.250 -0.2983 0.08363 0.08027 -0.0110 0.7959 0.0249
-6.000 -0.2799 0.08051 0.07708 -0.0147 0.7869 0.0260
-5.750 -0.2514 0.07829 0.07475 -0.0209 0.7777 0.0271
-4.750 -0.1564 0.06394 0.05992 -0.0353 0.7472 0.0284
-4.500 -0.1467 0.05997 0.05593 -0.0343 0.7407 0.0296
-4.250 -0.1257 0.05697 0.05285 -0.0358 0.7328 0.0313
-4.000 -0.1001 0.05409 0.04982 -0.0379 0.7265 0.0331
-3.750 -0.0701 0.05136 0.04695 -0.0405 0.7188 0.0356
-3.500 -0.0196 0.05125 0.04639 -0.0447 0.7124 0.0381
-3.250 -0.0025 0.04572 0.04082 -0.0458 0.7055 0.0393
-3.000 0.0136 0.04285 0.03788 -0.0456 0.6998 0.0416
-2.750 0.0407 0.04060 0.03552 -0.0468 0.6921 0.0451
-2.500 0.0876 0.04108 0.03543 -0.0483 0.6861 0.0506
-2.250 0.1047 0.03613 0.03053 -0.0491 0.6792 0.0525
-2.000 0.1272 0.03407 0.02837 -0.0493 0.6730 0.0556
-1.750 0.1654 0.03339 0.02722 -0.0500 0.6663 0.0645
-1.500 0.1862 0.03058 0.02442 -0.0504 0.6599 0.0668
-1.250 0.2125 0.02908 0.02279 -0.0506 0.6535 0.0718
-1.000 0.2443 0.02772 0.02110 -0.0508 0.6469 0.0793
-0.750 0.2693 0.02620 0.01948 -0.0510 0.6411 0.0841
-0.500 0.2988 0.02499 0.01805 -0.0512 0.6340 0.0941
-0.250 0.3273 0.02419 0.01696 -0.0511 0.6287 0.1065
0.000 0.3538 0.02286 0.01563 -0.0514 0.6213 0.1126
0.250 0.3817 0.02187 0.01444 -0.0513 0.6156 0.1236
0.500 0.4097 0.02101 0.01348 -0.0515 0.6088 0.1373
0.750 0.4372 0.02020 0.01253 -0.0515 0.6028 0.1536
1.000 0.4644 0.01941 0.01166 -0.0516 0.5966 0.1790
1.250 0.5026 0.01740 0.00887 -0.0500 0.5908 0.0737
1.500 0.5305 0.01680 0.00805 -0.0497 0.5858 0.0741
1.750 0.5589 0.01613 0.00735 -0.0496 0.5786 0.0718
2.000 0.5866 0.01556 0.00663 -0.0493 0.5733 0.0685
2.250 0.6141 0.01517 0.00623 -0.0491 0.5670 0.0670
2.500 0.6410 0.01486 0.00589 -0.0489 0.5609 0.0668
2.750 0.6679 0.01465 0.00570 -0.0487 0.5552 0.0680
3.000 0.6950 0.01450 0.00560 -0.0486 0.5486 0.0713
3.250 0.7218 0.01445 0.00548 -0.0483 0.5439 0.0776
3.500 0.7692 0.01280 0.00561 -0.0528 0.5365 1.0000
3.750 0.7955 0.01296 0.00562 -0.0524 0.5313 1.0000
4.000 0.8219 0.01316 0.00581 -0.0523 0.5252 1.0000
4.250 0.8483 0.01334 0.00599 -0.0521 0.5193 1.0000
4.500 0.8746 0.01355 0.00614 -0.0519 0.5143 1.0000
4.750 0.9002 0.01338 0.00591 -0.0513 0.5009 1.0000
5.000 0.9258 0.01316 0.00569 -0.0508 0.4825 1.0000
5.250 0.9516 0.01319 0.00574 -0.0505 0.4712 1.0000
5.500 0.9773 0.01313 0.00573 -0.0501 0.4531 1.0000
5.750 1.0023 0.01307 0.00560 -0.0496 0.4207 1.0000
6.000 1.0270 0.01327 0.00573 -0.0492 0.3819 1.0000
6.250 1.0478 0.01423 0.00617 -0.0487 0.2824 1.0000
6.500 1.0513 0.01825 0.00875 -0.0476 0.0377 1.0000
6.750 1.0731 0.01908 0.00970 -0.0469 0.0322 1.0000
7.000 1.0941 0.01995 0.01076 -0.0462 0.0303 1.0000
7.250 1.1131 0.02101 0.01202 -0.0453 0.0291 1.0000
7.500 1.1295 0.02228 0.01349 -0.0442 0.0285 1.0000
7.750 1.1419 0.02383 0.01517 -0.0429 0.0271 1.0000
8.000 1.1485 0.02575 0.01718 -0.0412 0.0255 1.0000
8.250 1.1526 0.02773 0.01927 -0.0392 0.0249 1.0000
8.500 1.1556 0.02957 0.02118 -0.0370 0.0248 1.0000
8.750 1.1610 0.03141 0.02306 -0.0350 0.0249 1.0000
9.000 1.1717 0.03299 0.02469 -0.0331 0.0253 1.0000
9.250 1.1884 0.03432 0.02610 -0.0311 0.0263 1.0000
9.500 1.2261 0.03592 0.02781 -0.0292 0.0299 1.0000
9.750 1.2930 0.03928 0.03135 -0.0300 0.0416 1.0000
16.250 0.7879 0.16938 0.16618 -0.0438 0.0783 1.0000
16.500 0.8147 0.16776 0.16460 -0.0386 0.0673 1.0000
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Polar data table (+)
Polar graphs
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