NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: NACA M19 AIRFOIL (m19-il) Reynolds number: 500,000 Max Cl/Cd: 82.98 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m19-il-500000-n5.txt Download as CSV file: xf-m19-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3796 0.10170 0.09874 0.0107 0.6768 0.0067
-7.500 -0.3729 0.09859 0.09562 0.0088 0.6701 0.0062
-7.250 -0.3667 0.09533 0.09234 0.0066 0.6643 0.0059
-7.000 -0.3559 0.09166 0.08866 0.0033 0.6582 0.0057
-6.500 -0.3283 0.08417 0.08110 -0.0039 0.6470 0.0058
-6.250 -0.3115 0.08043 0.07732 -0.0076 0.6413 0.0062
-6.000 -0.2915 0.07583 0.07264 -0.0124 0.6364 0.0069
-5.750 -0.2716 0.07191 0.06867 -0.0163 0.6310 0.0069
-5.500 -0.2498 0.06793 0.06462 -0.0202 0.6257 0.0068
-5.250 -0.2257 0.06366 0.06027 -0.0242 0.6208 0.0069
-5.000 -0.1992 0.05892 0.05544 -0.0285 0.6158 0.0071
-4.750 -0.1738 0.05564 0.05206 -0.0316 0.6106 0.0075
-4.500 -0.1479 0.05301 0.04935 -0.0340 0.6053 0.0079
-4.250 -0.1205 0.05018 0.04641 -0.0365 0.5998 0.0091
-4.000 -0.0882 0.04506 0.04110 -0.0401 0.5954 0.0101
-3.750 -0.0577 0.04105 0.03693 -0.0426 0.5907 0.0109
-3.500 -0.0313 0.03967 0.03544 -0.0437 0.5849 0.0117
-3.250 -0.0030 0.03770 0.03334 -0.0449 0.5797 0.0135
-3.000 0.0358 0.03107 0.02631 -0.0471 0.5758 0.0163
-2.750 0.0603 0.03088 0.02607 -0.0476 0.5697 0.0171
-2.500 0.0860 0.03024 0.02535 -0.0481 0.5643 0.0183
-2.250 0.1149 0.02834 0.02328 -0.0487 0.5589 0.0196
-2.000 0.1447 0.02625 0.02097 -0.0491 0.5536 0.0212
-1.750 0.1760 0.02400 0.01847 -0.0493 0.5488 0.0234
-1.500 0.2066 0.02141 0.01557 -0.0493 0.5437 0.0254
-1.250 0.2338 0.02006 0.01404 -0.0496 0.5382 0.0262
-1.000 0.2602 0.01977 0.01370 -0.0500 0.5326 0.0278
-0.750 0.2884 0.01867 0.01244 -0.0501 0.5271 0.0290
-0.250 0.3471 0.01455 0.00762 -0.0496 0.5174 0.0276
0.000 0.3753 0.01380 0.00669 -0.0497 0.5115 0.0288
0.250 0.4034 0.01321 0.00596 -0.0498 0.5061 0.0304
0.500 0.4316 0.01268 0.00530 -0.0498 0.5006 0.0314
0.750 0.4596 0.01226 0.00474 -0.0499 0.4953 0.0320
1.000 0.4876 0.01189 0.00430 -0.0499 0.4901 0.0325
1.250 0.5156 0.01170 0.00404 -0.0500 0.4842 0.0336
1.500 0.5434 0.01146 0.00373 -0.0501 0.4787 0.0339
1.750 0.5711 0.01107 0.00330 -0.0501 0.4730 0.0334
2.000 0.5987 0.01080 0.00299 -0.0501 0.4677 0.0330
2.250 0.6262 0.01059 0.00276 -0.0502 0.4628 0.0326
2.500 0.6538 0.01042 0.00259 -0.0502 0.4574 0.0322
2.750 0.6812 0.01032 0.00246 -0.0502 0.4515 0.0319
3.000 0.7089 0.01023 0.00239 -0.0503 0.4450 0.0317
3.250 0.7364 0.01020 0.00236 -0.0504 0.4383 0.0315
3.500 0.7641 0.01019 0.00235 -0.0505 0.4318 0.0313
3.750 0.7918 0.01021 0.00237 -0.0507 0.4257 0.0312
4.000 0.8193 0.01027 0.00241 -0.0508 0.4138 0.0312
4.250 0.8465 0.01041 0.00249 -0.0509 0.3959 0.0313
4.500 0.8736 0.01060 0.00260 -0.0511 0.3729 0.0318
4.750 0.9003 0.01085 0.00276 -0.0512 0.3483 0.0325
5.000 0.9252 0.01152 0.00310 -0.0513 0.2832 0.0344
5.250 0.9391 0.01448 0.00498 -0.0512 0.0224 0.1268
5.750 0.9988 0.01381 0.00600 -0.0531 0.0128 1.0000
6.000 1.0235 0.01424 0.00651 -0.0528 0.0111 1.0000
6.250 1.0472 0.01481 0.00717 -0.0525 0.0091 1.0000
6.500 1.0693 0.01565 0.00813 -0.0520 0.0081 1.0000
6.750 1.0920 0.01632 0.00888 -0.0516 0.0075 1.0000
7.000 1.1132 0.01715 0.00980 -0.0510 0.0069 1.0000
7.250 1.1336 0.01801 0.01073 -0.0504 0.0063 1.0000
7.500 1.1543 0.01872 0.01150 -0.0499 0.0057 1.0000
7.750 1.1680 0.02020 0.01306 -0.0487 0.0051 1.0000
8.000 1.1841 0.02130 0.01426 -0.0477 0.0049 1.0000
8.250 1.1965 0.02265 0.01572 -0.0463 0.0047 1.0000
8.500 1.2056 0.02419 0.01736 -0.0446 0.0045 1.0000
8.750 1.2100 0.02584 0.01911 -0.0425 0.0043 1.0000
9.000 1.2135 0.02772 0.02108 -0.0407 0.0041 1.0000
9.250 1.2191 0.02963 0.02308 -0.0392 0.0040 1.0000
9.500 1.2268 0.03146 0.02502 -0.0375 0.0039 1.0000
9.750 1.2372 0.03320 0.02682 -0.0356 0.0039 1.0000
10.000 1.2495 0.03482 0.02853 -0.0340 0.0037 1.0000
10.250 1.2605 0.03638 0.03016 -0.0330 0.0036 1.0000
10.500 1.2690 0.03803 0.03189 -0.0324 0.0034 1.0000
10.750 1.2769 0.04001 0.03396 -0.0314 0.0032 1.0000
11.000 1.2907 0.04213 0.03628 -0.0293 0.0030 1.0000
11.250 1.3037 0.04468 0.03905 -0.0274 0.0028 1.0000
11.500 1.3127 0.04768 0.04228 -0.0256 0.0027 1.0000
11.750 1.3172 0.05098 0.04582 -0.0241 0.0026 1.0000
12.000 1.3160 0.05448 0.04954 -0.0230 0.0026 1.0000
12.250 1.3109 0.05826 0.05355 -0.0221 0.0025 1.0000
12.500 1.3031 0.06224 0.05774 -0.0216 0.0025 1.0000
12.750 1.2932 0.06646 0.06217 -0.0214 0.0025 1.0000
13.000 1.2816 0.07097 0.06687 -0.0217 0.0025 1.0000
13.250 1.2684 0.07571 0.07180 -0.0223 0.0025 1.0000
13.500 1.2538 0.08078 0.07704 -0.0233 0.0025 1.0000
13.750 1.2384 0.08608 0.08251 -0.0248 0.0025 1.0000
14.000 1.2221 0.09171 0.08830 -0.0266 0.0025 1.0000
14.250 1.2055 0.09773 0.09448 -0.0290 0.0026 1.0000
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Polar data table (+)
Polar graphs
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