NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M19 AIRFOIL (m19-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.23 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m19-il-1000000-n5.txt Download as CSV file: xf-m19-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3988 0.10241 0.09983 0.0133 0.6333 0.0028
-7.750 -0.3929 0.09896 0.09638 0.0113 0.6278 0.0028
-7.500 -0.3876 0.09553 0.09294 0.0090 0.6230 0.0028
-7.250 -0.3781 0.09149 0.08889 0.0054 0.6185 0.0028
-7.000 -0.3659 0.08748 0.08487 0.0015 0.6136 0.0030
-6.750 -0.3508 0.08419 0.08154 -0.0020 0.6087 0.0031
-6.500 -0.3342 0.08090 0.07823 -0.0054 0.6039 0.0032
-6.250 -0.3161 0.07743 0.07472 -0.0090 0.5989 0.0034
-6.000 -0.2964 0.07362 0.07086 -0.0130 0.5944 0.0035
-5.750 -0.2750 0.06957 0.06676 -0.0170 0.5900 0.0038
-5.500 -0.2513 0.06482 0.06194 -0.0216 0.5854 0.0043
-5.250 -0.2247 0.05899 0.05601 -0.0269 0.5813 0.0046
-5.000 -0.1975 0.05456 0.05150 -0.0309 0.5772 0.0049
-4.750 -0.1714 0.05182 0.04867 -0.0334 0.5719 0.0053
-4.500 -0.1432 0.04815 0.04489 -0.0363 0.5670 0.0058
-4.250 -0.1120 0.04282 0.03939 -0.0399 0.5631 0.0070
-4.000 -0.0841 0.04037 0.03686 -0.0416 0.5579 0.0077
-3.750 -0.0561 0.03808 0.03444 -0.0430 0.5526 0.0085
-3.500 -0.0233 0.03226 0.02835 -0.0453 0.5488 0.0108
-3.250 0.0035 0.03152 0.02754 -0.0459 0.5431 0.0113
-3.000 0.0309 0.03039 0.02631 -0.0465 0.5375 0.0122
-2.750 0.0657 0.02307 0.01849 -0.0475 0.5343 0.0165
-2.500 0.0925 0.02306 0.01845 -0.0478 0.5284 0.0168
-2.000 0.1468 0.02190 0.01712 -0.0484 0.5174 0.0180
-1.750 0.1745 0.02104 0.01615 -0.0487 0.5120 0.0190
-1.500 0.2031 0.01950 0.01444 -0.0488 0.5071 0.0199
-1.250 0.2320 0.01753 0.01224 -0.0488 0.5019 0.0204
-1.000 0.2608 0.01544 0.00987 -0.0487 0.4963 0.0210
-0.750 0.2894 0.01279 0.00680 -0.0483 0.4918 0.0218
-0.500 0.3176 0.01212 0.00597 -0.0484 0.4866 0.0231
-0.250 0.3458 0.01195 0.00571 -0.0485 0.4812 0.0239
0.000 0.3740 0.01195 0.00566 -0.0486 0.4759 0.0244
0.250 0.4016 0.01093 0.00448 -0.0488 0.4701 0.0272
0.500 0.4296 0.01071 0.00420 -0.0490 0.4645 0.0283
0.750 0.4577 0.01046 0.00391 -0.0491 0.4593 0.0294
1.000 0.4858 0.01020 0.00359 -0.0493 0.4540 0.0303
1.250 0.5138 0.00991 0.00324 -0.0493 0.4493 0.0305
1.500 0.5417 0.00964 0.00293 -0.0494 0.4434 0.0306
1.750 0.5696 0.00950 0.00273 -0.0496 0.4363 0.0315
2.000 0.5974 0.00930 0.00250 -0.0496 0.4292 0.0315
2.250 0.6251 0.00910 0.00226 -0.0497 0.4232 0.0307
2.500 0.6529 0.00894 0.00208 -0.0498 0.4182 0.0299
2.750 0.6807 0.00883 0.00195 -0.0499 0.4119 0.0292
3.000 0.7086 0.00877 0.00187 -0.0500 0.4064 0.0286
3.250 0.7365 0.00872 0.00183 -0.0501 0.4017 0.0281
3.500 0.7643 0.00874 0.00182 -0.0503 0.3945 0.0277
3.750 0.7919 0.00884 0.00186 -0.0505 0.3765 0.0273
4.000 0.8193 0.00899 0.00193 -0.0507 0.3543 0.0271
4.250 0.8467 0.00918 0.00204 -0.0509 0.3343 0.0269
4.500 0.8727 0.00971 0.00230 -0.0511 0.2791 0.0268
4.750 0.8923 0.01189 0.00351 -0.0512 0.0751 0.0268
5.000 0.9174 0.01253 0.00396 -0.0512 0.0156 0.0270
5.250 0.9443 0.01272 0.00418 -0.0513 0.0130 0.0280
5.500 0.9709 0.01295 0.00447 -0.0514 0.0107 0.0338
6.000 1.0287 0.01210 0.00545 -0.0531 0.0073 1.0000
6.500 1.0788 0.01284 0.00624 -0.0527 0.0058 1.0000
6.750 1.1025 0.01344 0.00690 -0.0524 0.0051 1.0000
7.000 1.1272 0.01382 0.00730 -0.0523 0.0046 1.0000
7.250 1.1511 0.01430 0.00785 -0.0520 0.0041 1.0000
7.500 1.1745 0.01483 0.00842 -0.0517 0.0038 1.0000
7.750 1.1975 0.01539 0.00901 -0.0514 0.0035 1.0000
8.000 1.2174 0.01633 0.01004 -0.0508 0.0032 1.0000
8.250 1.2371 0.01722 0.01102 -0.0502 0.0030 1.0000
8.500 1.2556 0.01818 0.01207 -0.0494 0.0029 1.0000
8.750 1.2712 0.01936 0.01336 -0.0483 0.0027 1.0000
9.000 1.2835 0.02074 0.01488 -0.0469 0.0026 1.0000
9.250 1.2942 0.02212 0.01636 -0.0454 0.0024 1.0000
9.500 1.3042 0.02334 0.01766 -0.0439 0.0023 1.0000
9.750 1.3105 0.02474 0.01914 -0.0424 0.0022 1.0000
10.000 1.3199 0.02620 0.02067 -0.0418 0.0021 1.0000
10.250 1.3284 0.02788 0.02243 -0.0413 0.0020 1.0000
10.500 1.3367 0.02963 0.02425 -0.0408 0.0019 1.0000
10.750 1.3419 0.03170 0.02641 -0.0401 0.0019 1.0000
11.000 1.3453 0.03395 0.02875 -0.0393 0.0018 1.0000
11.250 1.3447 0.03654 0.03146 -0.0377 0.0018 1.0000
11.500 1.3439 0.03917 0.03425 -0.0352 0.0017 1.0000
11.750 1.3495 0.04131 0.03652 -0.0330 0.0017 1.0000
12.000 1.3622 0.04499 0.04051 -0.0270 0.0014 1.0000
12.250 1.3651 0.04957 0.04541 -0.0244 0.0013 1.0000
12.500 1.3591 0.05368 0.04975 -0.0231 0.0012 1.0000
12.750 1.3496 0.05793 0.05422 -0.0223 0.0012 1.0000
13.000 1.3380 0.06241 0.05889 -0.0219 0.0012 1.0000
13.250 1.3246 0.06708 0.06375 -0.0219 0.0012 1.0000
13.500 1.3094 0.07205 0.06889 -0.0224 0.0012 1.0000
13.750 1.2931 0.07724 0.07425 -0.0233 0.0012 1.0000
14.000 1.2755 0.08280 0.07996 -0.0247 0.0012 1.0000
14.250 1.2570 0.08864 0.08596 -0.0265 0.0012 1.0000
14.500 1.2388 0.09488 0.09235 -0.0289 0.0012 1.0000
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Polar data table (+)
Polar graphs
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