EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 550 AIRFOIL (e550-il) Reynolds number: 500,000 Max Cl/Cd: 99.6 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e550-il-500000.txt Download as CSV file: xf-e550-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 550 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6287 0.08307 0.08012 -0.0557 1.0000 0.0096
-14.250 -0.6478 0.07636 0.07330 -0.0592 1.0000 0.0095
-14.000 -0.6693 0.06993 0.06671 -0.0622 1.0000 0.0094
-13.750 -0.6920 0.06394 0.06055 -0.0645 1.0000 0.0094
-13.500 -0.7079 0.05936 0.05582 -0.0657 1.0000 0.0093
-13.250 -0.7243 0.05494 0.05124 -0.0665 1.0000 0.0092
-13.000 -0.7378 0.05104 0.04716 -0.0667 1.0000 0.0090
-12.750 -0.7501 0.04738 0.04332 -0.0665 1.0000 0.0089
-12.500 -0.7594 0.04417 0.03991 -0.0658 1.0000 0.0088
-12.250 -0.7683 0.04092 0.03643 -0.0647 1.0000 0.0087
-12.000 -0.7721 0.03829 0.03359 -0.0634 1.0000 0.0087
-11.750 -0.7719 0.03598 0.03109 -0.0619 1.0000 0.0086
-11.500 -0.7707 0.03401 0.02894 -0.0603 1.0000 0.0090
-11.250 -0.7649 0.03233 0.02713 -0.0586 1.0000 0.0089
-11.000 -0.7571 0.03086 0.02555 -0.0570 1.0000 0.0088
-10.750 -0.7503 0.02954 0.02410 -0.0551 1.0000 0.0091
-10.500 -0.7436 0.02834 0.02279 -0.0531 1.0000 0.0094
-10.250 -0.7097 0.02680 0.02111 -0.0557 0.9937 0.0096
-10.000 -0.6819 0.02531 0.01951 -0.0570 0.9574 0.0098
-9.750 -0.6192 0.02342 0.01757 -0.0655 0.9334 0.0103
-9.500 -0.5313 0.02173 0.01572 -0.0796 0.8969 0.0114
-9.250 -0.4970 0.02084 0.01452 -0.0825 0.8375 0.0119
-9.000 -0.4858 0.02018 0.01365 -0.0808 0.8011 0.0121
-8.750 -0.4807 0.01923 0.01255 -0.0784 0.7743 0.0127
-8.500 -0.4724 0.01847 0.01168 -0.0764 0.7530 0.0135
-8.250 -0.4627 0.01780 0.01091 -0.0744 0.7350 0.0142
-8.000 -0.4522 0.01724 0.01022 -0.0723 0.7194 0.0153
-7.750 -0.4523 0.01649 0.00939 -0.0687 0.7056 0.0164
-7.500 -0.4391 0.01602 0.00882 -0.0668 0.6930 0.0178
-7.250 -0.4262 0.01541 0.00816 -0.0649 0.6811 0.0199
-7.000 -0.4104 0.01488 0.00756 -0.0633 0.6703 0.0233
-6.500 -0.3766 0.01374 0.00643 -0.0606 0.6508 0.0445
-6.250 -0.3586 0.01316 0.00594 -0.0595 0.6424 0.0685
-6.000 -0.3391 0.01256 0.00548 -0.0587 0.6341 0.1036
-5.750 -0.3202 0.01190 0.00500 -0.0578 0.6268 0.1570
-5.500 -0.3035 0.01078 0.00435 -0.0570 0.6197 0.2602
-5.250 -0.2902 0.00920 0.00360 -0.0559 0.6132 0.4569
-5.000 -0.2634 0.00920 0.00368 -0.0558 0.6068 0.5194
-4.750 -0.2352 0.00933 0.00376 -0.0558 0.6002 0.5411
-4.500 -0.2070 0.00952 0.00382 -0.0558 0.5942 0.5548
-4.250 -0.1784 0.00965 0.00391 -0.0558 0.5885 0.5639
-4.000 -0.1499 0.00977 0.00394 -0.0559 0.5831 0.5716
-3.750 -0.1215 0.00999 0.00408 -0.0558 0.5782 0.5793
-3.500 -0.0928 0.01012 0.00413 -0.0560 0.5737 0.5864
-3.250 -0.0643 0.01036 0.00440 -0.0558 0.5690 0.5945
-3.000 -0.0361 0.01066 0.00465 -0.0556 0.5647 0.6047
-2.750 -0.0077 0.01088 0.00483 -0.0556 0.5604 0.6096
-2.500 0.0211 0.01084 0.00475 -0.0559 0.5564 0.6118
-2.250 0.0500 0.01081 0.00466 -0.0562 0.5524 0.6137
-2.000 0.0788 0.01080 0.00456 -0.0565 0.5488 0.6155
-1.750 0.1077 0.01085 0.00449 -0.0568 0.5454 0.6172
-1.500 0.1367 0.01083 0.00441 -0.0572 0.5422 0.6186
-1.250 0.1654 0.01074 0.00431 -0.0575 0.5390 0.6199
-1.000 0.1941 0.01070 0.00426 -0.0578 0.5356 0.6213
-0.750 0.2228 0.01071 0.00423 -0.0580 0.5325 0.6228
-0.500 0.2516 0.01076 0.00422 -0.0583 0.5294 0.6243
-0.250 0.2805 0.01080 0.00423 -0.0587 0.5266 0.6257
0.000 0.3094 0.01079 0.00422 -0.0590 0.5240 0.6272
0.250 0.3382 0.01080 0.00421 -0.0593 0.5212 0.6288
0.500 0.3671 0.01082 0.00420 -0.0597 0.5183 0.6304
0.750 0.3959 0.01086 0.00420 -0.0600 0.5155 0.6321
1.000 0.4250 0.01097 0.00423 -0.0604 0.5129 0.6338
1.250 0.4540 0.01104 0.00428 -0.0608 0.5105 0.6352
1.500 0.4824 0.01100 0.00428 -0.0611 0.5080 0.6367
1.750 0.5109 0.01100 0.00431 -0.0613 0.5053 0.6382
2.000 0.5394 0.01103 0.00436 -0.0616 0.5027 0.6397
2.250 0.5681 0.01109 0.00441 -0.0619 0.5003 0.6413
2.500 0.5968 0.01117 0.00448 -0.0622 0.4977 0.6430
2.750 0.6257 0.01132 0.00461 -0.0626 0.4951 0.6448
3.000 0.6538 0.01135 0.00469 -0.0628 0.4928 0.6469
3.250 0.6821 0.01140 0.00477 -0.0631 0.4900 0.6490
3.500 0.7105 0.01146 0.00483 -0.0633 0.4871 0.6508
3.750 0.7388 0.01150 0.00488 -0.0636 0.4843 0.6525
4.000 0.7670 0.01157 0.00495 -0.0639 0.4814 0.6544
4.250 0.7952 0.01169 0.00510 -0.0641 0.4784 0.6563
4.500 0.8225 0.01171 0.00520 -0.0642 0.4754 0.6582
4.750 0.8501 0.01175 0.00530 -0.0643 0.4720 0.6604
5.000 0.8779 0.01180 0.00538 -0.0644 0.4687 0.6627
5.250 0.9058 0.01190 0.00547 -0.0646 0.4655 0.6650
5.500 0.9336 0.01204 0.00563 -0.0648 0.4620 0.6674
5.750 0.9601 0.01204 0.00573 -0.0647 0.4582 0.6699
6.000 0.9869 0.01206 0.00582 -0.0647 0.4542 0.6724
6.250 1.0138 0.01211 0.00590 -0.0647 0.4502 0.6749
6.500 1.0408 0.01224 0.00606 -0.0647 0.4462 0.6776
6.750 1.0666 0.01226 0.00619 -0.0645 0.4416 0.6804
7.000 1.0929 0.01231 0.00628 -0.0644 0.4369 0.6834
7.250 1.1193 0.01242 0.00639 -0.0644 0.4322 0.6862
7.500 1.1442 0.01243 0.00655 -0.0640 0.4270 0.6891
7.750 1.1692 0.01246 0.00666 -0.0636 0.4209 0.6923
8.000 1.1940 0.01258 0.00680 -0.0633 0.4149 0.6959
8.250 1.2185 0.01262 0.00695 -0.0629 0.4072 0.6999
8.500 1.2419 0.01273 0.00709 -0.0623 0.3996 0.7037
8.750 1.2654 0.01280 0.00727 -0.0617 0.3900 0.7077
9.000 1.2878 0.01294 0.00747 -0.0609 0.3792 0.7121
9.250 1.3088 0.01314 0.00770 -0.0600 0.3661 0.7168
9.500 1.3279 0.01339 0.00797 -0.0587 0.3499 0.7214
9.750 1.3434 0.01377 0.00834 -0.0568 0.3294 0.7264
10.000 1.3540 0.01432 0.00882 -0.0542 0.3063 0.7322
10.250 1.3582 0.01495 0.00939 -0.0505 0.2833 0.7380
10.500 1.3610 0.01572 0.01011 -0.0468 0.2628 0.7448
10.750 1.3634 0.01657 0.01092 -0.0432 0.2430 0.7524
11.000 1.3636 0.01753 0.01187 -0.0396 0.2251 0.7611
11.250 1.3619 0.01865 0.01298 -0.0360 0.2088 0.7713
11.750 1.3549 0.02146 0.01584 -0.0298 0.1794 0.7987
12.000 1.3501 0.02316 0.01761 -0.0271 0.1664 0.8189
12.250 1.3442 0.02500 0.01957 -0.0246 0.1549 0.8526
12.500 1.3410 0.02704 0.02181 -0.0233 0.1429 1.0000
12.750 1.3360 0.02959 0.02433 -0.0221 0.1320 1.0000
13.000 1.3321 0.03217 0.02689 -0.0213 0.1219 1.0000
13.250 1.3289 0.03476 0.02949 -0.0206 0.1127 1.0000
13.500 1.3238 0.03761 0.03232 -0.0200 0.1044 1.0000
13.750 1.3191 0.04048 0.03519 -0.0195 0.0964 1.0000
14.000 1.3157 0.04330 0.03803 -0.0192 0.0890 1.0000
14.250 1.3097 0.04647 0.04119 -0.0190 0.0820 1.0000
14.500 1.3077 0.04934 0.04409 -0.0189 0.0753 1.0000
14.750 1.3041 0.05246 0.04722 -0.0190 0.0696 1.0000
15.000 1.3012 0.05560 0.05037 -0.0192 0.0636 1.0000
15.250 1.2996 0.05866 0.05345 -0.0195 0.0587 1.0000
15.500 1.2964 0.06199 0.05679 -0.0200 0.0538 1.0000
15.750 1.2952 0.06517 0.06001 -0.0205 0.0496 1.0000
16.000 1.2929 0.06853 0.06338 -0.0211 0.0454 1.0000
16.250 1.2916 0.07186 0.06676 -0.0218 0.0421 1.0000
16.500 1.2904 0.07523 0.07015 -0.0226 0.0388 1.0000
16.750 1.2874 0.07891 0.07387 -0.0235 0.0360 1.0000
17.000 1.2876 0.08223 0.07725 -0.0245 0.0332 1.0000
17.250 1.2827 0.08629 0.08133 -0.0257 0.0307 1.0000
17.500 1.2840 0.08958 0.08470 -0.0267 0.0285 1.0000
17.750 1.2819 0.09339 0.08854 -0.0280 0.0266 1.0000
18.000 1.2780 0.09754 0.09275 -0.0295 0.0248 1.0000
18.250 1.2788 0.10102 0.09630 -0.0308 0.0230 1.0000
18.500 1.2745 0.10534 0.10066 -0.0325 0.0216 1.0000
18.750 1.2713 0.10955 0.10495 -0.0342 0.0203 1.0000
19.000 1.2709 0.11337 0.10885 -0.0358 0.0190 1.0000
19.250 1.2666 0.11785 0.11338 -0.0378 0.0178 1.0000
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Polar data table (+)
Polar graphs
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