EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 541 AIRFOIL (e541-il) Reynolds number: 200,000 Max Cl/Cd: 46.82 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e541-il-200000.txt Download as CSV file: xf-e541-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 541 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2492 0.09217 0.08903 -0.0892 0.9699 0.0534
-11.500 -0.2632 0.08399 0.08086 -0.0955 0.9679 0.0548
-11.250 -0.2864 0.07501 0.07183 -0.1020 0.9644 0.0550
-11.000 -0.3163 0.06744 0.06414 -0.1068 0.9611 0.0552
-10.750 -0.3429 0.06150 0.05803 -0.1095 0.9578 0.0555
-10.500 -0.3701 0.05724 0.05355 -0.1104 0.9527 0.0559
-10.250 -0.3921 0.05448 0.05056 -0.1095 0.9453 0.0562
-10.000 -0.4182 0.05301 0.04885 -0.1059 0.9359 0.0565
-8.500 -0.4678 0.04175 0.03559 -0.0893 0.9124 0.0327
-8.250 -0.4635 0.03621 0.02940 -0.0848 0.9065 0.0235
-8.000 -0.4360 0.03151 0.02442 -0.0855 0.9042 0.0218
-7.750 -0.4025 0.02853 0.02107 -0.0865 0.9024 0.0211
-7.500 -0.3450 0.02565 0.01785 -0.0915 0.9026 0.0210
-7.250 -0.2948 0.02391 0.01595 -0.0947 0.9022 0.0221
-7.000 -0.2589 0.02249 0.01449 -0.0960 0.9007 0.0256
-6.750 -0.2376 0.02193 0.01393 -0.0953 0.8976 0.0289
-6.500 -0.2230 0.02145 0.01339 -0.0931 0.8928 0.0326
-6.250 -0.2138 0.02050 0.01246 -0.0903 0.8886 0.0410
-6.000 -0.2050 0.01958 0.01163 -0.0875 0.8854 0.0623
-5.750 -0.2158 0.01881 0.01134 -0.0815 0.8797 0.1289
-5.500 -0.2313 0.01791 0.01101 -0.0748 0.8741 0.2392
-5.250 -0.2541 0.01745 0.01096 -0.0665 0.8687 0.3249
-5.000 -0.2829 0.01753 0.01134 -0.0567 0.8616 0.3843
-4.750 -0.2521 0.02028 0.01557 -0.0519 0.8604 0.7147
-4.500 -0.1742 0.02361 0.01864 -0.0568 0.8613 0.7452
-4.250 -0.0639 0.02572 0.02042 -0.0688 0.8645 0.7581
-4.000 -0.0167 0.02654 0.02109 -0.0714 0.8632 0.7683
-3.750 0.0587 0.02770 0.02208 -0.0781 0.8638 0.7831
-3.500 0.0965 0.02812 0.02240 -0.0795 0.8620 0.7954
-3.250 0.1169 0.02839 0.02259 -0.0784 0.8595 0.8059
-3.000 0.1642 0.02813 0.02224 -0.0821 0.8585 0.8104
-2.750 0.1795 0.02837 0.02240 -0.0802 0.8561 0.8214
-2.500 0.2226 0.02819 0.02217 -0.0833 0.8538 0.8256
-2.250 0.2342 0.02858 0.02255 -0.0808 0.8500 0.8364
-2.000 0.2776 0.02834 0.02225 -0.0840 0.8483 0.8430
-1.750 0.3617 0.02808 0.02196 -0.0931 0.8491 0.8807
-1.500 0.3898 0.02796 0.02181 -0.0937 0.8467 0.8925
-1.250 0.4109 0.02821 0.02204 -0.0930 0.8443 0.9040
-1.000 0.4548 0.02719 0.02099 -0.0969 0.8430 0.9077
-0.750 0.4677 0.02764 0.02147 -0.0949 0.8389 0.9187
-0.500 0.5012 0.02709 0.02094 -0.0970 0.8357 0.9234
-0.250 0.5207 0.02723 0.02108 -0.0961 0.8325 0.9331
0.000 0.5590 0.02648 0.02033 -0.0990 0.8305 0.9371
0.250 0.5827 0.02655 0.02040 -0.0987 0.8283 0.9462
0.500 0.6082 0.02628 0.02021 -0.0995 0.8228 0.9517
0.750 0.6320 0.02619 0.02013 -0.0995 0.8188 0.9595
1.000 0.6696 0.02547 0.01945 -0.1021 0.8162 0.9640
1.250 0.6998 0.02515 0.01914 -0.1030 0.8136 0.9708
1.500 0.7254 0.02487 0.01894 -0.1037 0.8063 0.9771
1.750 0.7599 0.02427 0.01838 -0.1055 0.8027 0.9836
2.000 0.7995 0.02330 0.01744 -0.1082 0.7998 0.9868
3.000 0.6159 0.02807 0.02223 -0.0543 0.7638 0.9162
3.250 0.6502 0.02729 0.02148 -0.0555 0.7606 0.9162
3.500 0.6916 0.02633 0.02055 -0.0580 0.7583 0.9163
3.750 0.6828 0.02655 0.02084 -0.0517 0.7484 0.9143
4.000 0.7235 0.02557 0.01992 -0.0539 0.7454 0.9147
4.250 0.7141 0.02563 0.02003 -0.0474 0.7365 0.9122
4.500 0.4309 0.02756 0.02168 0.0095 0.7096 0.9100
4.750 0.5021 0.02639 0.02061 0.0022 0.7103 0.9096
5.000 0.5813 0.02538 0.01973 -0.0070 0.7095 0.9094
5.250 0.8146 0.02271 0.01735 -0.0448 0.7133 0.9114
5.500 0.8006 0.02249 0.01718 -0.0369 0.7042 0.9110
5.750 0.7012 0.02269 0.01728 -0.0129 0.6942 0.9108
6.000 0.7809 0.02141 0.01614 -0.0222 0.6889 0.9108
6.250 0.7190 0.02124 0.01596 -0.0056 0.6787 0.9115
6.500 0.7692 0.02020 0.01500 -0.0093 0.6711 0.9116
6.750 0.7642 0.01957 0.01441 -0.0031 0.6604 0.9128
7.000 0.7489 0.01914 0.01403 0.0047 0.6483 0.9144
7.250 0.7563 0.01866 0.01361 0.0083 0.6342 0.9153
7.500 0.7759 0.01812 0.01313 0.0097 0.6173 0.9159
7.750 0.7814 0.01804 0.01311 0.0131 0.5950 0.9169
8.000 0.8018 0.01770 0.01276 0.0143 0.5659 0.9177
8.250 0.8202 0.01752 0.01245 0.0159 0.5274 0.9188
8.500 0.8306 0.01775 0.01247 0.0186 0.4839 0.9201
8.750 0.8344 0.01833 0.01284 0.0218 0.4410 0.9213
9.000 0.8354 0.01913 0.01345 0.0251 0.4002 0.9226
9.250 0.8347 0.02011 0.01423 0.0283 0.3597 0.9240
9.500 0.8351 0.02118 0.01516 0.0311 0.3209 0.9254
9.750 0.8369 0.02232 0.01615 0.0335 0.2835 0.9269
10.000 0.8399 0.02353 0.01720 0.0355 0.2493 0.9283
10.250 0.8440 0.02477 0.01831 0.0373 0.2160 0.9300
10.500 0.8485 0.02611 0.01951 0.0389 0.1830 0.9316
10.750 0.8517 0.02743 0.02069 0.0407 0.1534 0.9330
11.000 0.8556 0.02884 0.02197 0.0423 0.1263 0.9344
11.250 0.8601 0.03031 0.02334 0.0438 0.1034 0.9359
11.500 0.8632 0.03194 0.02487 0.0453 0.0860 0.9375
11.750 0.8667 0.03366 0.02653 0.0466 0.0723 0.9392
12.000 0.8730 0.03528 0.02815 0.0476 0.0615 0.9408
12.250 0.8804 0.03691 0.02987 0.0485 0.0537 0.9425
12.500 0.8853 0.03880 0.03171 0.0494 0.0477 0.9440
12.750 0.8972 0.04018 0.03324 0.0498 0.0426 0.9457
13.000 0.9040 0.04186 0.03493 0.0504 0.0380 0.9477
13.250 0.9126 0.04357 0.03676 0.0512 0.0338 0.9499
13.500 0.9216 0.04525 0.03854 0.0516 0.0302 0.9525
13.750 0.9280 0.04750 0.04081 0.0523 0.0261 0.9545
14.000 0.9362 0.04937 0.04287 0.0523 0.0233 0.9571
14.250 0.9445 0.05141 0.04503 0.0524 0.0212 0.9594
14.500 0.9525 0.05387 0.04754 0.0527 0.0192 0.9613
14.750 0.9612 0.05686 0.05078 0.0532 0.0182 0.9631
15.000 0.9634 0.05966 0.05386 0.0530 0.0171 0.9663
15.250 0.9652 0.06276 0.05719 0.0525 0.0162 0.9696
15.500 0.9677 0.06559 0.06020 0.0509 0.0150 0.9738
15.750 0.9678 0.06902 0.06378 0.0493 0.0141 0.9787
16.000 0.9645 0.07264 0.06759 0.0483 0.0138 1.0000
16.250 0.9595 0.07696 0.07210 0.0469 0.0135 1.0000
16.500 0.9522 0.08175 0.07708 0.0452 0.0133 1.0000
16.750 0.9415 0.08720 0.08273 0.0430 0.0131 1.0000
17.000 0.9269 0.09346 0.08923 0.0402 0.0130 1.0000
17.250 0.9147 0.09962 0.09561 0.0368 0.0131 1.0000
17.500 0.8971 0.10701 0.10322 0.0327 0.0130 1.0000
17.750 0.8803 0.11477 0.11120 0.0278 0.0131 1.0000
18.000 0.8553 0.12498 0.12171 0.0211 0.0136 1.0000
18.250 0.7611 0.15476 0.15193 0.0042 0.0168 1.0000
18.500 0.7392 0.16648 0.16361 -0.0016 0.0185 1.0000
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