EPPLER 637 AIRFOIL (e637-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 637 AIRFOIL (e637-il) Reynolds number: 50,000 Max Cl/Cd: 14.86 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e637-il-50000.txt Download as CSV file: xf-e637-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 637 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3995 0.11712 0.11101 -0.0103 1.0000 0.1800
-9.000 -0.3625 0.11026 0.10413 -0.0071 1.0000 0.1918
-8.750 -0.3885 0.10990 0.10394 -0.0111 1.0000 0.1961
-8.500 -0.3600 0.10433 0.09839 -0.0087 1.0000 0.2096
-8.250 -0.3505 0.10059 0.09473 -0.0084 1.0000 0.2204
-8.000 -0.3747 0.09958 0.09390 -0.0114 1.0000 0.2282
-7.750 -0.3642 0.09591 0.09032 -0.0104 1.0000 0.2438
-7.500 -0.3594 0.09270 0.08722 -0.0098 1.0000 0.2597
-7.250 -0.3589 0.08985 0.08450 -0.0092 1.0000 0.2760
-7.000 -0.3351 0.08579 0.08051 -0.0067 1.0000 0.3009
-6.750 -0.3424 0.08366 0.07855 -0.0057 1.0000 0.3231
-6.500 -0.3281 0.08052 0.07553 -0.0033 1.0000 0.3532
-6.250 -0.3222 0.07816 0.07332 -0.0006 1.0000 0.3866
-6.000 -0.3036 0.07551 0.07080 0.0031 1.0000 0.4344
-5.750 -0.2817 0.07321 0.06863 0.0080 1.0000 0.5007
-5.500 -0.2076 0.06902 0.06442 0.0124 1.0000 0.6283
-5.250 -0.0817 0.06137 0.05667 0.0066 1.0000 0.8150
-4.500 -0.1314 0.05764 0.05339 -0.0035 0.9385 0.6820
-4.250 -0.2071 0.05459 0.05040 -0.0126 0.9032 0.5681
-4.000 -0.2049 0.04604 0.03969 -0.0463 0.8748 0.2229
-3.750 -0.1659 0.04278 0.03536 -0.0475 0.8592 0.1593
-3.500 -0.1363 0.04043 0.03241 -0.0470 0.8437 0.1429
-3.250 -0.1083 0.03928 0.03036 -0.0454 0.8286 0.1315
-3.000 -0.0796 0.03690 0.02780 -0.0451 0.8144 0.1285
-2.750 -0.0489 0.03511 0.02564 -0.0445 0.8013 0.1246
-2.500 -0.0186 0.03372 0.02387 -0.0438 0.7881 0.1230
-2.250 0.0101 0.03276 0.02264 -0.0432 0.7745 0.1261
-2.000 0.0424 0.03193 0.02150 -0.0431 0.7617 0.1323
-1.750 0.2693 0.02429 0.01635 -0.0708 0.7448 1.0000
-1.500 0.2895 0.02477 0.01641 -0.0697 0.7327 1.0000
-1.250 0.3095 0.02519 0.01646 -0.0683 0.7226 1.0000
-1.000 0.3289 0.02579 0.01682 -0.0675 0.7111 1.0000
-0.750 0.3481 0.02647 0.01726 -0.0666 0.7008 1.0000
-0.500 0.3681 0.02697 0.01750 -0.0652 0.6922 1.0000
-0.250 0.3860 0.02790 0.01829 -0.0647 0.6821 1.0000
0.000 0.4058 0.02847 0.01863 -0.0632 0.6744 1.0000
0.250 0.4226 0.02953 0.01960 -0.0627 0.6649 1.0000
0.500 0.4420 0.03024 0.02014 -0.0614 0.6581 1.0000
0.750 0.4566 0.03152 0.02136 -0.0608 0.6493 1.0000
1.000 0.4773 0.03211 0.02176 -0.0592 0.6432 1.0000
1.250 0.4867 0.03391 0.02357 -0.0587 0.6347 1.0000
1.500 0.5061 0.03470 0.02423 -0.0574 0.6288 1.0000
1.750 0.5127 0.03666 0.02618 -0.0564 0.6215 1.0000
2.000 0.5254 0.03803 0.02749 -0.0552 0.6151 1.0000
2.250 0.5416 0.03921 0.02858 -0.0538 0.6099 1.0000
2.500 0.5337 0.04212 0.03152 -0.0523 0.6037 1.0000
2.750 0.5455 0.04360 0.03294 -0.0508 0.5983 1.0000
3.000 0.5547 0.04535 0.03463 -0.0494 0.5935 1.0000
3.250 0.5320 0.04897 0.03825 -0.0469 0.5905 1.0000
3.500 0.5149 0.05203 0.04127 -0.0443 0.5882 1.0000
3.750 0.4956 0.05488 0.04407 -0.0410 0.5876 1.0000
4.000 0.4797 0.05763 0.04675 -0.0382 0.5889 1.0000
4.250 0.4744 0.06025 0.04933 -0.0366 0.5915 1.0000
4.500 0.4745 0.06292 0.05197 -0.0359 0.5965 1.0000
4.750 0.3247 0.06975 0.05896 -0.0328 0.7585 1.0000
5.000 0.3361 0.07139 0.06054 -0.0320 0.7454 1.0000
5.250 0.3509 0.07330 0.06239 -0.0316 0.7324 1.0000
5.500 0.3794 0.07630 0.06534 -0.0331 0.7226 1.0000
5.750 0.3916 0.07786 0.06686 -0.0323 0.7091 1.0000
6.000 0.3968 0.07923 0.06820 -0.0308 0.6962 1.0000
6.250 0.4079 0.08117 0.07011 -0.0302 0.6846 1.0000
6.500 0.4427 0.08487 0.07379 -0.0322 0.6753 1.0000
6.750 0.4428 0.08571 0.07462 -0.0302 0.6619 1.0000
7.000 0.4470 0.08732 0.07622 -0.0290 0.6504 1.0000
7.250 0.4713 0.09054 0.07944 -0.0299 0.6421 1.0000
7.750 0.4836 0.09381 0.08271 -0.0280 0.6174 1.0000
8.000 0.5046 0.09701 0.08593 -0.0286 0.6096 1.0000
8.250 0.5174 0.09904 0.08801 -0.0282 0.5970 1.0000
8.500 0.5168 0.10058 0.08956 -0.0270 0.5855 1.0000
8.750 0.5428 0.10444 0.09345 -0.0281 0.5783 1.0000
9.000 0.5462 0.10587 0.09492 -0.0271 0.5656 1.0000
9.250 0.5466 0.10768 0.09675 -0.0262 0.5548 1.0000
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Polar data table (+)
Polar graphs
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