EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 540 AIRFOIL (e540-il) Reynolds number: 200,000 Max Cl/Cd: 54.02 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e540-il-200000.txt Download as CSV file: xf-e540-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4175 0.10411 0.10079 -0.0620 1.0000 0.0469
-11.500 -0.4283 0.09939 0.09613 -0.0634 1.0000 0.0474
-11.250 -0.4488 0.09406 0.09090 -0.0647 1.0000 0.0480
-8.750 -0.5420 0.03748 0.03107 -0.0792 0.9354 0.0227
-8.500 -0.5096 0.03466 0.02799 -0.0807 0.9324 0.0213
-8.250 -0.4756 0.03067 0.02360 -0.0826 0.9304 0.0207
-8.000 -0.4319 0.02775 0.02034 -0.0856 0.9292 0.0204
-7.750 -0.3788 0.02545 0.01779 -0.0896 0.9291 0.0211
-7.500 -0.3340 0.02355 0.01582 -0.0919 0.9274 0.0244
-7.250 -0.3050 0.02270 0.01494 -0.0924 0.9213 0.0279
-7.000 -0.2713 0.02165 0.01382 -0.0936 0.9173 0.0303
-6.750 -0.2560 0.02043 0.01260 -0.0921 0.9100 0.0349
-6.500 -0.2402 0.01951 0.01169 -0.0908 0.9031 0.0465
-6.250 -0.2377 0.01849 0.01081 -0.0872 0.8949 0.0743
-6.000 -0.2461 0.01701 0.00992 -0.0824 0.8871 0.1703
-5.750 -0.2664 0.01630 0.00960 -0.0748 0.8769 0.2468
-5.500 -0.2882 0.01532 0.00916 -0.0670 0.8689 0.3571
-5.250 -0.2869 0.01632 0.01166 -0.0593 0.8632 0.6481
-5.000 -0.2740 0.01698 0.01212 -0.0563 0.8589 0.6908
-4.750 -0.1959 0.02103 0.01601 -0.0598 0.8593 0.7111
-4.500 -0.1317 0.02307 0.01785 -0.0634 0.8586 0.7223
-4.250 -0.1096 0.02381 0.01848 -0.0616 0.8539 0.7338
-4.000 0.0176 0.02601 0.02039 -0.0757 0.8579 0.7436
-3.750 0.0693 0.02665 0.02091 -0.0789 0.8556 0.7527
-3.500 0.0822 0.02678 0.02099 -0.0764 0.8503 0.7631
-3.250 0.1260 0.02674 0.02084 -0.0792 0.8477 0.7671
-3.000 0.1398 0.02666 0.02068 -0.0773 0.8439 0.7768
-2.750 0.1802 0.02659 0.02054 -0.0796 0.8408 0.7804
-2.500 0.1806 0.02669 0.02063 -0.0752 0.8352 0.7904
-2.250 0.2277 0.02645 0.02031 -0.0788 0.8330 0.7937
-2.000 0.2558 0.02631 0.02009 -0.0793 0.8302 0.7994
-1.750 0.2758 0.02628 0.02005 -0.0782 0.8263 0.8067
-1.500 0.3033 0.02620 0.01996 -0.0785 0.8225 0.8114
-1.250 0.3074 0.02619 0.01992 -0.0748 0.8180 0.8189
-1.000 0.3584 0.02587 0.01956 -0.0792 0.8163 0.8236
-0.750 0.4658 0.02585 0.01954 -0.0916 0.8168 0.8776
-0.500 0.3561 0.02599 0.01971 -0.0702 0.8061 0.8308
-0.250 0.4136 0.02562 0.01931 -0.0758 0.8043 0.8367
0.000 0.4392 0.02540 0.01907 -0.0759 0.8015 0.8399
0.250 0.4404 0.02547 0.01918 -0.0718 0.7960 0.8406
0.500 0.4465 0.02538 0.01910 -0.0685 0.7910 0.8420
0.750 0.4564 0.02515 0.01886 -0.0658 0.7876 0.8435
1.000 0.4365 0.02536 0.01911 -0.0577 0.7804 0.8440
1.250 0.4104 0.02525 0.01899 -0.0483 0.7748 0.8450
1.500 0.4429 0.02485 0.01858 -0.0496 0.7724 0.8465
1.750 0.4179 0.02510 0.01889 -0.0405 0.7637 0.8475
2.000 0.4529 0.02474 0.01853 -0.0422 0.7607 0.8485
2.250 0.4943 0.02433 0.01813 -0.0450 0.7584 0.8496
2.500 0.4525 0.02455 0.01839 -0.0330 0.7487 0.8505
2.750 0.4871 0.02411 0.01797 -0.0345 0.7458 0.8516
3.000 0.4713 0.02414 0.01804 -0.0273 0.7378 0.8528
3.250 0.4968 0.02372 0.01763 -0.0274 0.7335 0.8534
3.500 0.5374 0.02316 0.01709 -0.0299 0.7307 0.8543
3.750 0.5270 0.02322 0.01721 -0.0239 0.7219 0.8560
4.000 0.5650 0.02266 0.01667 -0.0260 0.7182 0.8564
4.250 0.6117 0.02204 0.01605 -0.0297 0.7154 0.8568
4.500 0.6093 0.02203 0.01613 -0.0251 0.7059 0.8582
4.750 0.6554 0.02136 0.01548 -0.0286 0.7021 0.8590
5.000 0.6656 0.02122 0.01542 -0.0259 0.6932 0.8600
5.250 0.7091 0.02056 0.01479 -0.0288 0.6883 0.8603
5.500 0.7232 0.02033 0.01467 -0.0265 0.6791 0.8611
5.750 0.7680 0.01964 0.01400 -0.0295 0.6731 0.8615
6.000 0.7807 0.01938 0.01385 -0.0269 0.6625 0.8625
6.250 0.8035 0.01898 0.01353 -0.0260 0.6526 0.8636
6.500 0.8322 0.01848 0.01310 -0.0261 0.6424 0.8648
6.750 0.8561 0.01802 0.01270 -0.0254 0.6301 0.8659
7.000 0.8715 0.01768 0.01244 -0.0232 0.6157 0.8671
7.250 0.8821 0.01743 0.01228 -0.0203 0.5989 0.8684
7.500 0.8928 0.01717 0.01208 -0.0173 0.5792 0.8697
7.750 0.9046 0.01697 0.01190 -0.0147 0.5561 0.8711
8.000 0.9156 0.01695 0.01182 -0.0119 0.5241 0.8726
8.250 0.9246 0.01716 0.01191 -0.0090 0.4861 0.8743
8.500 0.9271 0.01763 0.01219 -0.0049 0.4455 0.8759
8.750 0.9272 0.01835 0.01272 -0.0010 0.4052 0.8775
9.000 0.9259 0.01925 0.01344 0.0028 0.3655 0.8793
9.250 0.9250 0.02029 0.01432 0.0062 0.3286 0.8812
9.500 0.9244 0.02146 0.01533 0.0092 0.2928 0.8830
9.750 0.9251 0.02273 0.01645 0.0117 0.2591 0.8849
10.000 0.9275 0.02406 0.01764 0.0138 0.2265 0.8868
10.250 0.9284 0.02538 0.01885 0.0161 0.1970 0.8889
10.500 0.9294 0.02677 0.02013 0.0184 0.1692 0.8909
10.750 0.9309 0.02828 0.02152 0.0203 0.1420 0.8929
11.000 0.9330 0.02990 0.02302 0.0220 0.1187 0.8949
11.250 0.9350 0.03161 0.02465 0.0236 0.0987 0.8970
11.500 0.9359 0.03352 0.02646 0.0251 0.0836 0.8991
11.750 0.9392 0.03537 0.02827 0.0263 0.0713 0.9011
12.000 0.9451 0.03689 0.02984 0.0275 0.0617 0.9032
12.250 0.9489 0.03864 0.03165 0.0288 0.0550 0.9055
12.500 0.9537 0.04040 0.03342 0.0298 0.0492 0.9079
12.750 0.9605 0.04215 0.03526 0.0307 0.0441 0.9107
13.000 0.9682 0.04386 0.03704 0.0311 0.0396 0.9137
13.250 0.9733 0.04594 0.03914 0.0320 0.0354 0.9164
13.500 0.9807 0.04764 0.04101 0.0326 0.0317 0.9196
13.750 0.9855 0.04971 0.04311 0.0330 0.0285 0.9229
14.000 0.9934 0.05189 0.04539 0.0336 0.0256 0.9259
14.250 0.9999 0.05400 0.04772 0.0338 0.0231 0.9297
14.500 1.0049 0.05619 0.05002 0.0342 0.0212 0.9340
14.750 1.0111 0.05895 0.05285 0.0348 0.0191 0.9376
15.000 1.0152 0.06195 0.05610 0.0351 0.0183 0.9425
15.250 1.0155 0.06482 0.05923 0.0346 0.0172 0.9504
15.500 1.0175 0.06822 0.06289 0.0338 0.0166 0.9602
15.750 1.0155 0.07165 0.06656 0.0328 0.0161 1.0000
16.000 1.0145 0.07518 0.07020 0.0311 0.0149 1.0000
16.250 1.0103 0.07954 0.07476 0.0295 0.0146 1.0000
16.500 1.0050 0.08414 0.07953 0.0276 0.0143 1.0000
16.750 0.9976 0.08914 0.08472 0.0254 0.0140 1.0000
17.000 0.9847 0.09529 0.09113 0.0226 0.0141 1.0000
17.250 0.9750 0.10097 0.09694 0.0196 0.0137 1.0000
17.500 0.9598 0.10794 0.10414 0.0157 0.0137 1.0000
17.750 0.9380 0.11659 0.11307 0.0107 0.0140 1.0000
18.000 0.9115 0.12676 0.12351 0.0045 0.0144 1.0000
18.250 0.8677 0.14204 0.13911 -0.0050 0.0153 1.0000
18.500 0.7755 0.17617 0.17340 -0.0219 0.0205 1.0000
18.750 0.7754 0.18222 0.17942 -0.0256 0.0199 1.0000
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