EPPLER 545 AIRFOIL (e545-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 545 AIRFOIL (e545-il) Reynolds number: 200,000 Max Cl/Cd: 64.29 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e545-il-200000.txt Download as CSV file: xf-e545-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 545 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4581 0.08812 0.08473 -0.0667 1.0000 0.0572
-11.250 -0.4908 0.08105 0.07763 -0.0702 1.0000 0.0574
-11.000 -0.5215 0.07589 0.07242 -0.0715 1.0000 0.0575
-10.750 -0.5517 0.07191 0.06840 -0.0711 1.0000 0.0576
-10.500 -0.5840 0.06903 0.06550 -0.0687 1.0000 0.0578
-10.250 -0.6166 0.06777 0.06426 -0.0638 1.0000 0.0573
-10.000 -0.6433 0.06547 0.06188 -0.0624 0.9959 0.0579
-9.750 -0.6692 0.06040 0.05624 -0.0667 0.9799 0.0610
-9.500 -0.6908 0.04063 0.03454 -0.0623 0.9699 0.0221
-9.250 -0.6648 0.03731 0.03093 -0.0634 0.9636 0.0211
-9.000 -0.6352 0.03394 0.02718 -0.0648 0.9584 0.0205
-8.750 -0.5974 0.03110 0.02400 -0.0670 0.9558 0.0200
-8.500 -0.5551 0.02884 0.02148 -0.0694 0.9543 0.0202
-8.250 -0.5148 0.02715 0.01966 -0.0712 0.9501 0.0207
-8.000 -0.4723 0.02558 0.01799 -0.0729 0.9472 0.0222
-7.750 -0.4337 0.02429 0.01674 -0.0751 0.9432 0.0243
-7.500 -0.3943 0.02304 0.01545 -0.0783 0.9395 0.0286
-7.250 -0.3673 0.02183 0.01426 -0.0796 0.9295 0.0331
-7.000 -0.3381 0.02016 0.01265 -0.0820 0.9224 0.0415
-6.750 -0.3272 0.01888 0.01143 -0.0809 0.9080 0.0552
-6.500 -0.3239 0.01754 0.01029 -0.0783 0.8936 0.0871
-6.250 -0.3257 0.01602 0.00925 -0.0750 0.8801 0.1670
-6.000 -0.3313 0.01400 0.00804 -0.0714 0.8687 0.3304
-5.750 -0.3288 0.01366 0.00880 -0.0667 0.8565 0.5497
-5.500 -0.2964 0.01467 0.00965 -0.0664 0.8503 0.5976
-5.250 -0.2705 0.01584 0.01077 -0.0646 0.8409 0.6180
-5.000 -0.2372 0.01698 0.01180 -0.0639 0.8343 0.6323
-4.750 -0.2115 0.01763 0.01232 -0.0628 0.8261 0.6452
-4.500 -0.1749 0.01914 0.01381 -0.0616 0.8191 0.6519
-4.250 -0.1472 0.01947 0.01394 -0.0613 0.8130 0.6637
-4.000 -0.1085 0.02134 0.01584 -0.0596 0.8058 0.6692
-3.750 -0.0799 0.02216 0.01656 -0.0583 0.7990 0.6827
-3.500 -0.0375 0.02308 0.01737 -0.0586 0.7940 0.6861
-3.250 -0.0139 0.02314 0.01737 -0.0576 0.7857 0.6902
-3.000 -0.0060 0.02211 0.01618 -0.0566 0.7785 0.7001
-2.750 0.0218 0.02215 0.01615 -0.0561 0.7724 0.7018
-2.500 0.0473 0.02212 0.01607 -0.0555 0.7655 0.7040
-2.250 0.0750 0.02198 0.01582 -0.0555 0.7597 0.7067
-2.000 0.0952 0.02168 0.01545 -0.0548 0.7529 0.7104
-1.750 0.1080 0.02070 0.01432 -0.0550 0.7453 0.7176
-1.500 0.1367 0.02051 0.01404 -0.0550 0.7400 0.7188
-1.250 0.1593 0.02041 0.01393 -0.0541 0.7330 0.7204
-1.000 0.1843 0.02021 0.01366 -0.0537 0.7263 0.7221
-0.750 0.2125 0.02000 0.01335 -0.0541 0.7212 0.7240
-0.500 0.2338 0.01982 0.01317 -0.0535 0.7147 0.7265
-0.250 0.2583 0.01952 0.01283 -0.0537 0.7090 0.7286
0.000 0.2861 0.01922 0.01242 -0.0546 0.7043 0.7310
0.250 0.3115 0.01894 0.01209 -0.0553 0.6990 0.7339
0.500 0.3367 0.01866 0.01177 -0.0560 0.6932 0.7358
0.750 0.3636 0.01847 0.01155 -0.0561 0.6884 0.7369
1.000 0.3928 0.01837 0.01139 -0.0566 0.6844 0.7382
1.250 0.4148 0.01835 0.01143 -0.0558 0.6785 0.7398
1.500 0.4403 0.01827 0.01136 -0.0557 0.6732 0.7413
1.750 0.4693 0.01813 0.01119 -0.0564 0.6685 0.7427
2.000 0.4965 0.01806 0.01110 -0.0568 0.6635 0.7443
2.250 0.5207 0.01798 0.01105 -0.0566 0.6573 0.7460
2.500 0.5493 0.01786 0.01091 -0.0573 0.6522 0.7479
2.750 0.5808 0.01779 0.01078 -0.0585 0.6481 0.7501
3.000 0.6045 0.01775 0.01081 -0.0585 0.6416 0.7524
3.250 0.6325 0.01764 0.01069 -0.0590 0.6355 0.7540
3.500 0.6624 0.01753 0.01056 -0.0596 0.6307 0.7552
3.750 0.6850 0.01753 0.01066 -0.0589 0.6243 0.7567
4.000 0.7107 0.01747 0.01064 -0.0588 0.6178 0.7583
4.250 0.7415 0.01738 0.01052 -0.0595 0.6123 0.7599
4.500 0.7632 0.01739 0.01064 -0.0587 0.6049 0.7618
4.750 0.7906 0.01730 0.01056 -0.0589 0.5978 0.7640
5.000 0.8184 0.01728 0.01056 -0.0592 0.5914 0.7665
5.250 0.8425 0.01727 0.01064 -0.0589 0.5837 0.7690
5.500 0.8731 0.01722 0.01056 -0.0598 0.5775 0.7711
5.750 0.8954 0.01722 0.01070 -0.0591 0.5699 0.7729
6.000 0.9205 0.01716 0.01069 -0.0587 0.5622 0.7747
6.250 0.9449 0.01715 0.01077 -0.0582 0.5544 0.7768
6.500 0.9679 0.01713 0.01084 -0.0575 0.5455 0.7791
6.750 0.9927 0.01714 0.01091 -0.0572 0.5371 0.7816
7.000 1.0151 0.01708 0.01093 -0.0564 0.5261 0.7844
7.250 1.0353 0.01706 0.01098 -0.0552 0.5131 0.7875
7.500 1.0556 0.01702 0.01100 -0.0540 0.4996 0.7904
7.750 1.0731 0.01701 0.01105 -0.0522 0.4851 0.7932
8.000 1.0889 0.01705 0.01116 -0.0501 0.4687 0.7961
8.250 1.1025 0.01715 0.01132 -0.0477 0.4497 0.7994
8.500 1.1138 0.01733 0.01151 -0.0450 0.4282 0.8031
8.750 1.1209 0.01760 0.01172 -0.0416 0.4051 0.8069
9.000 1.1242 0.01800 0.01209 -0.0376 0.3801 0.8103
9.250 1.1254 0.01863 0.01263 -0.0335 0.3545 0.8144
9.500 1.1285 0.01936 0.01331 -0.0300 0.3309 0.8191
9.750 1.1315 0.02023 0.01411 -0.0269 0.3095 0.8243
10.000 1.1325 0.02111 0.01497 -0.0235 0.2909 0.8293
10.250 1.1341 0.02211 0.01595 -0.0204 0.2731 0.8354
10.500 1.1366 0.02324 0.01705 -0.0179 0.2556 0.8419
10.750 1.1364 0.02441 0.01824 -0.0150 0.2387 0.8483
11.000 1.1361 0.02580 0.01961 -0.0126 0.2218 0.8563
11.250 1.1348 0.02731 0.02111 -0.0101 0.2057 0.8648
11.500 1.1348 0.02892 0.02275 -0.0082 0.1884 0.8758
11.750 1.1361 0.03041 0.02435 -0.0063 0.1654 0.8899
12.000 1.1333 0.03226 0.02617 -0.0045 0.1407 0.9151
12.250 1.1281 0.03480 0.02862 -0.0039 0.1266 1.0000
12.500 1.1252 0.03755 0.03129 -0.0035 0.1153 1.0000
12.750 1.1259 0.04003 0.03376 -0.0032 0.1044 1.0000
13.000 1.1280 0.04243 0.03616 -0.0029 0.0941 1.0000
13.250 1.1303 0.04483 0.03855 -0.0027 0.0849 1.0000
13.500 1.1317 0.04737 0.04109 -0.0026 0.0767 1.0000
13.750 1.1323 0.05002 0.04372 -0.0024 0.0698 1.0000
14.000 1.1321 0.05280 0.04647 -0.0023 0.0639 1.0000
14.250 1.1321 0.05562 0.04928 -0.0024 0.0587 1.0000
14.500 1.1343 0.05831 0.05204 -0.0025 0.0537 1.0000
14.750 1.1354 0.06113 0.05488 -0.0026 0.0495 1.0000
15.000 1.1359 0.06404 0.05774 -0.0029 0.0459 1.0000
15.250 1.1382 0.06694 0.06075 -0.0033 0.0421 1.0000
15.500 1.1393 0.06995 0.06381 -0.0037 0.0390 1.0000
15.750 1.1409 0.07293 0.06679 -0.0043 0.0363 1.0000
16.000 1.1413 0.07621 0.07019 -0.0050 0.0333 1.0000
16.250 1.1431 0.07922 0.07318 -0.0056 0.0311 1.0000
16.500 1.1432 0.08271 0.07681 -0.0066 0.0288 1.0000
16.750 1.1451 0.08583 0.07994 -0.0074 0.0269 1.0000
17.000 1.1440 0.08957 0.08381 -0.0087 0.0249 1.0000
17.250 1.1471 0.09256 0.08683 -0.0093 0.0234 1.0000
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Polar data table (+)
Polar graphs
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