EPPLER 360 AIRFOIL (e360-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 360 AIRFOIL (e360-il) Reynolds number: 50,000 Max Cl/Cd: 31.47 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e360-il-50000-n5.txt Download as CSV file: xf-e360-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 360 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5063 0.09652 0.08930 -0.0277 1.0000 0.0426
-10.000 -0.5417 0.08462 0.07736 -0.0381 1.0000 0.0397
-9.750 -0.5484 0.08050 0.07324 -0.0395 1.0000 0.0394
-9.500 -0.5622 0.07617 0.06889 -0.0405 1.0000 0.0392
-9.250 -0.5767 0.07244 0.06513 -0.0402 1.0000 0.0390
-9.000 -0.5906 0.06924 0.06186 -0.0387 1.0000 0.0388
-8.750 -0.6019 0.06585 0.05837 -0.0371 1.0000 0.0385
-8.500 -0.6104 0.06249 0.05485 -0.0352 1.0000 0.0383
-8.250 -0.6165 0.05918 0.05134 -0.0330 1.0000 0.0382
-8.000 -0.6198 0.05594 0.04786 -0.0307 1.0000 0.0380
-7.750 -0.6208 0.05278 0.04441 -0.0281 1.0000 0.0380
-7.500 -0.6192 0.04974 0.04105 -0.0254 1.0000 0.0381
-7.250 -0.6153 0.04686 0.03780 -0.0226 1.0000 0.0386
-7.000 -0.6091 0.04419 0.03471 -0.0198 1.0000 0.0393
-6.750 -0.5999 0.04177 0.03204 -0.0174 1.0000 0.0405
-6.500 -0.5875 0.03997 0.03017 -0.0155 1.0000 0.0421
-6.250 -0.5747 0.03805 0.02804 -0.0133 1.0000 0.0436
-6.000 -0.5603 0.03608 0.02579 -0.0111 1.0000 0.0450
-5.750 -0.5439 0.03416 0.02355 -0.0090 1.0000 0.0466
-5.500 -0.5265 0.03258 0.02167 -0.0069 1.0000 0.0487
-5.250 -0.5123 0.03131 0.02048 -0.0051 1.0000 0.0523
-5.000 -0.4960 0.03020 0.01923 -0.0031 1.0000 0.0564
-4.750 -0.4791 0.02907 0.01803 -0.0011 1.0000 0.0605
-4.500 -0.4433 0.02785 0.01666 -0.0027 0.9922 0.0711
-4.250 -0.4059 0.02646 0.01533 -0.0049 0.9815 0.0873
-4.000 -0.3721 0.02506 0.01405 -0.0067 0.9695 0.1176
-3.750 -0.3434 0.02320 0.01279 -0.0080 0.9571 0.1954
-3.500 -0.3301 0.02063 0.01254 -0.0056 0.9453 0.5485
-3.250 -0.2933 0.02155 0.01383 -0.0030 0.9365 0.7659
-3.000 -0.2420 0.02300 0.01497 -0.0031 0.9314 0.8466
-2.750 -0.1518 0.02434 0.01582 -0.0107 0.9337 0.8996
-2.500 -0.0855 0.02429 0.01538 -0.0176 0.9281 0.9173
-2.250 -0.0341 0.02407 0.01488 -0.0225 0.9175 0.9298
-2.000 0.0181 0.02378 0.01432 -0.0276 0.9070 0.9391
-1.750 0.0678 0.02346 0.01378 -0.0323 0.8966 0.9472
-1.500 0.1126 0.02318 0.01330 -0.0362 0.8844 0.9550
-1.250 0.1546 0.02292 0.01289 -0.0395 0.8718 0.9619
-1.000 0.1953 0.02268 0.01250 -0.0425 0.8597 0.9687
-0.750 0.2344 0.02246 0.01215 -0.0452 0.8482 0.9749
-0.500 0.2714 0.02227 0.01185 -0.0475 0.8359 0.9811
-0.250 0.3060 0.02213 0.01164 -0.0495 0.8236 0.9871
0.000 0.3407 0.02200 0.01145 -0.0514 0.8119 0.9931
0.250 0.3760 0.02185 0.01123 -0.0533 0.8016 0.9985
0.500 0.3986 0.02194 0.01130 -0.0529 0.7893 1.0000
0.750 0.4179 0.02208 0.01142 -0.0518 0.7776 1.0000
1.000 0.4383 0.02220 0.01151 -0.0508 0.7672 1.0000
1.250 0.4575 0.02235 0.01167 -0.0495 0.7561 1.0000
1.500 0.4760 0.02256 0.01189 -0.0483 0.7445 1.0000
1.750 0.4960 0.02270 0.01204 -0.0471 0.7337 1.0000
2.000 0.5163 0.02281 0.01216 -0.0458 0.7225 1.0000
2.250 0.5338 0.02299 0.01238 -0.0441 0.7092 1.0000
2.500 0.5514 0.02313 0.01254 -0.0423 0.6956 1.0000
2.750 0.5690 0.02322 0.01265 -0.0403 0.6812 1.0000
3.000 0.5865 0.02327 0.01274 -0.0382 0.6660 1.0000
3.250 0.6035 0.02331 0.01278 -0.0359 0.6500 1.0000
3.500 0.6203 0.02332 0.01281 -0.0336 0.6333 1.0000
3.750 0.6368 0.02334 0.01285 -0.0313 0.6162 1.0000
4.000 0.6532 0.02335 0.01291 -0.0288 0.5987 1.0000
4.250 0.6695 0.02335 0.01294 -0.0264 0.5809 1.0000
4.500 0.6856 0.02335 0.01294 -0.0239 0.5621 1.0000
4.750 0.6986 0.02348 0.01316 -0.0212 0.5408 1.0000
5.000 0.7128 0.02354 0.01327 -0.0185 0.5187 1.0000
5.250 0.7258 0.02366 0.01343 -0.0157 0.4941 1.0000
5.500 0.7388 0.02376 0.01353 -0.0128 0.4665 1.0000
5.750 0.7508 0.02395 0.01370 -0.0098 0.4353 1.0000
6.000 0.7621 0.02422 0.01389 -0.0067 0.3999 1.0000
6.250 0.7727 0.02463 0.01409 -0.0036 0.3634 1.0000
6.500 0.7820 0.02525 0.01449 -0.0006 0.3292 1.0000
6.750 0.7908 0.02605 0.01505 0.0023 0.3002 1.0000
7.000 0.8001 0.02695 0.01579 0.0050 0.2760 1.0000
7.250 0.8102 0.02791 0.01661 0.0075 0.2571 1.0000
7.500 0.8217 0.02890 0.01748 0.0097 0.2406 1.0000
7.750 0.8345 0.02990 0.01842 0.0117 0.2263 1.0000
8.000 0.8490 0.03090 0.01943 0.0133 0.2135 1.0000
8.250 0.8650 0.03194 0.02052 0.0148 0.2024 1.0000
8.500 0.8815 0.03299 0.02156 0.0161 0.1925 1.0000
8.750 0.8988 0.03406 0.02266 0.0173 0.1834 1.0000
9.000 0.9174 0.03523 0.02394 0.0183 0.1752 1.0000
9.250 0.9365 0.03636 0.02507 0.0192 0.1676 1.0000
9.500 0.9527 0.03768 0.02660 0.0204 0.1602 1.0000
9.750 0.9720 0.03894 0.02790 0.0212 0.1539 1.0000
10.000 0.9880 0.04045 0.02959 0.0222 0.1479 1.0000
10.250 1.0017 0.04191 0.03124 0.0234 0.1419 1.0000
10.500 1.0214 0.04337 0.03269 0.0240 0.1368 1.0000
10.750 1.0276 0.04537 0.03507 0.0258 0.1322 1.0000
11.000 1.0369 0.04708 0.03694 0.0272 0.1276 1.0000
11.250 1.0549 0.04861 0.03843 0.0278 0.1231 1.0000
11.500 1.0479 0.05104 0.04126 0.0304 0.1202 1.0000
11.750 1.0427 0.05362 0.04415 0.0324 0.1174 1.0000
12.000 1.0403 0.05612 0.04685 0.0339 0.1145 1.0000
12.250 1.0504 0.05791 0.04867 0.0346 0.1111 1.0000
12.500 1.0437 0.06089 0.05182 0.0356 0.1089 1.0000
12.750 1.0184 0.06535 0.05659 0.0360 0.1077 1.0000
13.000 0.9881 0.07089 0.06240 0.0350 0.1069 1.0000
13.250 0.9495 0.07830 0.07004 0.0322 0.1068 1.0000
13.500 0.8939 0.08960 0.08146 0.0261 0.1073 1.0000
13.750 0.8184 0.10798 0.09986 0.0150 0.1079 1.0000
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Polar data table (+)
Polar graphs
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