EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 540 AIRFOIL (e540-il) Reynolds number: 50,000 Max Cl/Cd: 20.11 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e540-il-50000-n5.txt Download as CSV file: xf-e540-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 540 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4249 0.10977 0.10279 -0.0635 1.0000 0.0359
-12.000 -0.4397 0.10220 0.09530 -0.0670 1.0000 0.0346
-11.750 -0.4951 0.09007 0.08304 -0.0738 1.0000 0.0311
-11.500 -0.5126 0.08618 0.07916 -0.0737 1.0000 0.0309
-11.250 -0.5342 0.08260 0.07557 -0.0728 1.0000 0.0307
-11.000 -0.5561 0.07968 0.07264 -0.0708 1.0000 0.0306
-10.750 -0.5806 0.07737 0.07033 -0.0677 1.0000 0.0305
-10.500 -0.6062 0.07560 0.06856 -0.0637 1.0000 0.0304
-10.250 -0.6331 0.07419 0.06714 -0.0590 1.0000 0.0302
-10.000 -0.6609 0.07300 0.06592 -0.0538 1.0000 0.0302
-9.750 -0.6876 0.07186 0.06473 -0.0486 0.9997 0.0301
-9.500 -0.6952 0.06850 0.06107 -0.0482 0.9911 0.0300
-9.250 -0.6978 0.06502 0.05723 -0.0477 0.9830 0.0302
-9.000 -0.6994 0.06174 0.05352 -0.0463 0.9743 0.0305
-8.750 -0.6955 0.05874 0.05005 -0.0451 0.9669 0.0309
-8.500 -0.6872 0.05544 0.04646 -0.0446 0.9605 0.0321
-8.250 -0.6733 0.05298 0.04381 -0.0444 0.9550 0.0338
-8.000 -0.6591 0.05070 0.04123 -0.0435 0.9489 0.0350
-7.750 -0.6349 0.04807 0.03819 -0.0438 0.9449 0.0363
-7.500 -0.6067 0.04560 0.03531 -0.0439 0.9413 0.0377
-7.250 -0.5694 0.04339 0.03268 -0.0447 0.9383 0.0402
-7.000 -0.5205 0.04157 0.03074 -0.0475 0.9370 0.0457
-6.750 -0.4456 0.04000 0.02892 -0.0525 0.9389 0.0571
-6.500 -0.4168 0.03905 0.02793 -0.0525 0.9348 0.0697
-6.250 -0.3941 0.03788 0.02683 -0.0522 0.9309 0.0889
-6.000 -0.3864 0.03676 0.02591 -0.0497 0.9249 0.1154
-5.750 -0.3854 0.03534 0.02498 -0.0467 0.9185 0.1677
-5.500 -0.3973 0.03382 0.02421 -0.0419 0.9115 0.2541
-4.750 -0.3080 0.04229 0.03369 -0.0288 0.9010 0.7435
-4.500 -0.2262 0.04425 0.03510 -0.0344 0.9016 0.7804
-4.250 -0.1927 0.04439 0.03494 -0.0353 0.8978 0.7955
-4.000 -0.1768 0.04433 0.03463 -0.0339 0.8923 0.8061
-3.750 -0.1460 0.04405 0.03409 -0.0353 0.8889 0.8143
-3.500 -0.1120 0.04368 0.03345 -0.0374 0.8863 0.8212
-3.250 -0.1102 0.04376 0.03342 -0.0336 0.8790 0.8291
-3.000 -0.0846 0.04349 0.03296 -0.0342 0.8752 0.8348
-2.750 -0.0518 0.04316 0.03240 -0.0361 0.8725 0.8397
-2.500 -0.0606 0.04335 0.03253 -0.0306 0.8649 0.8468
-2.250 -0.0309 0.04310 0.03212 -0.0319 0.8612 0.8505
-2.000 -0.0034 0.04287 0.03173 -0.0329 0.8582 0.8548
-1.750 -0.0160 0.04312 0.03195 -0.0267 0.8504 0.8608
-1.500 0.0117 0.04295 0.03164 -0.0277 0.8467 0.8638
-1.250 0.0409 0.04275 0.03132 -0.0290 0.8437 0.8670
-1.000 0.0207 0.04308 0.03163 -0.0214 0.8354 0.8727
-0.750 0.0447 0.04296 0.03143 -0.0218 0.8316 0.8754
-0.500 0.0703 0.04289 0.03126 -0.0224 0.8280 0.8778
-0.250 0.0673 0.04310 0.03144 -0.0180 0.8206 0.8816
0.000 0.0835 0.04305 0.03133 -0.0168 0.8165 0.8846
0.250 0.0735 0.04322 0.03149 -0.0111 0.8092 0.8885
0.500 0.0937 0.04323 0.03146 -0.0108 0.8043 0.8904
0.750 0.1230 0.04316 0.03132 -0.0119 0.8009 0.8922
1.000 0.1131 0.04341 0.03158 -0.0064 0.7926 0.8957
1.250 0.1288 0.04336 0.03150 -0.0050 0.7879 0.8980
1.500 0.1125 0.04347 0.03160 0.0018 0.7798 0.9018
1.750 0.1369 0.04351 0.03163 0.0015 0.7749 0.9033
2.000 0.1501 0.04361 0.03173 0.0030 0.7687 0.9051
2.250 0.1617 0.04372 0.03185 0.0048 0.7619 0.9073
2.500 0.1908 0.04367 0.03180 0.0040 0.7580 0.9090
2.750 0.1795 0.04387 0.03201 0.0096 0.7483 0.9123
3.000 0.2032 0.04376 0.03192 0.0098 0.7440 0.9139
3.250 0.1991 0.04399 0.03219 0.0140 0.7343 0.9166
3.500 0.2325 0.04398 0.03222 0.0125 0.7299 0.9179
3.750 0.2363 0.04430 0.03258 0.0152 0.7200 0.9205
4.000 0.2683 0.04421 0.03255 0.0141 0.7155 0.9219
4.250 0.2671 0.04449 0.03287 0.0178 0.7050 0.9246
4.500 0.2801 0.04457 0.03303 0.0195 0.6972 0.9270
4.750 0.2968 0.04459 0.03312 0.0206 0.6895 0.9295
5.000 0.3133 0.04491 0.03353 0.0213 0.6798 0.9316
5.250 0.3464 0.04481 0.03354 0.0201 0.6739 0.9332
5.500 0.3568 0.04514 0.03399 0.0217 0.6627 0.9358
5.750 0.3735 0.04530 0.03425 0.0227 0.6532 0.9381
6.000 0.4012 0.04512 0.03419 0.0225 0.6459 0.9401
6.250 0.4110 0.04540 0.03459 0.0243 0.6342 0.9432
6.500 0.4328 0.04564 0.03500 0.0242 0.6232 0.9455
6.750 0.4718 0.04513 0.03468 0.0227 0.6165 0.9472
7.000 0.4888 0.04538 0.03509 0.0233 0.6037 0.9503
7.250 0.5062 0.04555 0.03542 0.0240 0.5910 0.9534
7.500 0.5241 0.04564 0.03571 0.0248 0.5782 0.9566
8.000 0.5739 0.04549 0.03599 0.0244 0.5518 0.9617
8.250 0.5997 0.04522 0.03593 0.0243 0.5382 0.9649
8.500 0.6257 0.04478 0.03572 0.0244 0.5241 0.9686
8.750 0.6549 0.04416 0.03540 0.0242 0.5092 0.9720
9.000 0.6869 0.04330 0.03480 0.0240 0.4930 0.9756
9.250 0.7225 0.04197 0.03373 0.0238 0.4757 0.9796
9.500 0.7460 0.04169 0.03366 0.0241 0.4521 0.9848
9.750 0.7749 0.04079 0.03296 0.0245 0.4261 0.9911
10.000 0.7964 0.04021 0.03243 0.0258 0.3969 1.0000
10.250 0.8054 0.04008 0.03226 0.0285 0.3688 1.0000
10.500 0.8136 0.04045 0.03255 0.0307 0.3388 1.0000
10.750 0.8197 0.04128 0.03328 0.0325 0.3080 1.0000
11.000 0.8241 0.04252 0.03441 0.0340 0.2782 1.0000
11.250 0.8277 0.04407 0.03586 0.0351 0.2500 1.0000
11.500 0.8301 0.04591 0.03760 0.0360 0.2228 1.0000
11.750 0.8326 0.04793 0.03954 0.0367 0.1979 1.0000
12.000 0.8349 0.05010 0.04158 0.0372 0.1760 1.0000
12.250 0.8379 0.05242 0.04389 0.0374 0.1550 1.0000
12.500 0.8411 0.05481 0.04626 0.0376 0.1378 1.0000
12.750 0.8442 0.05730 0.04866 0.0375 0.1227 1.0000
13.000 0.8494 0.05975 0.05113 0.0375 0.1096 1.0000
13.250 0.8549 0.06229 0.05373 0.0373 0.0978 1.0000
13.500 0.8606 0.06492 0.05647 0.0371 0.0874 1.0000
13.750 0.8708 0.06726 0.05890 0.0371 0.0797 1.0000
14.000 0.8775 0.06986 0.06155 0.0368 0.0727 1.0000
14.250 0.8830 0.07285 0.06476 0.0364 0.0664 1.0000
14.500 0.8889 0.07572 0.06776 0.0359 0.0613 1.0000
14.750 0.8993 0.07850 0.07066 0.0357 0.0573 1.0000
15.000 0.8968 0.08274 0.07528 0.0347 0.0542 1.0000
15.250 0.8928 0.08699 0.07975 0.0334 0.0513 1.0000
15.500 0.8930 0.09050 0.08329 0.0321 0.0484 1.0000
15.750 0.8888 0.09512 0.08805 0.0305 0.0466 1.0000
16.000 0.8747 0.10148 0.09472 0.0278 0.0460 1.0000
16.250 0.8580 0.10855 0.10207 0.0242 0.0457 1.0000
16.500 0.8385 0.11657 0.11031 0.0198 0.0457 1.0000
16.750 0.8171 0.12559 0.11951 0.0145 0.0459 1.0000
17.000 0.7948 0.13566 0.12971 0.0085 0.0462 1.0000
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