EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 520 AIRFOIL (e520-il) Reynolds number: 50,000 Max Cl/Cd: 28.39 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e520-il-50000.txt Download as CSV file: xf-e520-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 520 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6157 0.13574 0.12877 0.0019 1.0000 0.2023
-12.750 -0.5919 0.13254 0.12549 0.0032 1.0000 0.2132
-12.500 -0.7961 0.08828 0.08171 -0.0309 1.0000 0.1312
-12.250 -0.8203 0.08142 0.07479 -0.0334 1.0000 0.1303
-12.000 -0.8489 0.07522 0.06850 -0.0352 1.0000 0.1293
-11.750 -0.8764 0.06992 0.06306 -0.0358 1.0000 0.1285
-11.500 -0.9033 0.06538 0.05834 -0.0352 1.0000 0.1280
-11.250 -0.9275 0.06153 0.05427 -0.0331 1.0000 0.1282
-11.000 -0.9469 0.05782 0.05023 -0.0307 1.0000 0.1291
-10.750 -0.9624 0.05423 0.04619 -0.0281 1.0000 0.1307
-10.500 -0.9445 0.05151 0.04358 -0.0276 1.0000 0.1406
-10.250 -0.9546 0.04837 0.03988 -0.0247 1.0000 0.1451
-10.000 -0.9352 0.04558 0.03716 -0.0241 1.0000 0.1563
-9.750 -0.9232 0.04323 0.03475 -0.0228 1.0000 0.1692
-9.500 -0.9103 0.04086 0.03229 -0.0214 1.0000 0.1834
-9.250 -0.8999 0.03881 0.03015 -0.0196 1.0000 0.2005
-9.000 -0.8843 0.03688 0.02832 -0.0182 1.0000 0.2208
-8.750 -0.8734 0.03533 0.02680 -0.0161 1.0000 0.2435
-8.500 -0.8617 0.03393 0.02560 -0.0138 1.0000 0.2681
-8.250 -0.8627 0.03274 0.02436 -0.0098 1.0000 0.2905
-8.000 -0.8554 0.03178 0.02366 -0.0065 1.0000 0.3172
-7.750 -0.8512 0.03095 0.02302 -0.0027 1.0000 0.3454
-7.500 -0.8467 0.03018 0.02240 0.0011 1.0000 0.3762
-7.250 -0.8410 0.02958 0.02197 0.0049 1.0000 0.4099
-7.000 -0.8268 0.02958 0.02224 0.0084 1.0000 0.4473
-6.750 -0.8150 0.02976 0.02252 0.0122 1.0000 0.4840
-6.500 -0.7864 0.03156 0.02447 0.0155 1.0000 0.5196
-6.250 -0.7563 0.03376 0.02663 0.0189 1.0000 0.5498
-6.000 -0.7251 0.03610 0.02885 0.0222 1.0000 0.5758
-5.750 -0.7125 0.03700 0.02960 0.0263 1.0000 0.6006
-5.500 -0.6612 0.04034 0.03272 0.0281 1.0000 0.6211
-5.250 -0.6598 0.04029 0.03258 0.0325 1.0000 0.6443
-5.000 -0.6101 0.04254 0.03460 0.0332 1.0000 0.6640
-4.750 -0.6034 0.04247 0.03439 0.0368 1.0000 0.6861
-4.500 -0.5682 0.04326 0.03500 0.0376 1.0000 0.7064
-4.250 -0.5390 0.04355 0.03513 0.0384 1.0000 0.7274
-4.000 -0.5320 0.04310 0.03458 0.0415 1.0000 0.7486
-3.750 -0.4742 0.04347 0.03470 0.0378 1.0000 0.7690
-3.500 -0.4628 0.04296 0.03408 0.0398 1.0000 0.7897
-3.250 -0.4212 0.04270 0.03366 0.0373 1.0000 0.8093
-3.000 -0.3822 0.04233 0.03313 0.0349 1.0000 0.8285
-2.750 -0.3600 0.04180 0.03250 0.0347 1.0000 0.8472
-2.500 -0.3457 0.04125 0.03187 0.0355 1.0000 0.8653
-2.250 -0.3045 0.04077 0.03126 0.0319 1.0000 0.8821
-2.000 -0.2698 0.04029 0.03069 0.0291 1.0000 0.8984
-1.750 -0.2372 0.03982 0.03014 0.0264 1.0000 0.9141
-1.500 -0.2052 0.03939 0.02962 0.0235 1.0000 0.9290
-1.250 -0.1721 0.03900 0.02918 0.0202 1.0000 0.9433
-1.000 -0.1391 0.03867 0.02879 0.0168 1.0000 0.9568
-0.750 -0.1049 0.03842 0.02850 0.0130 1.0000 0.9696
-0.500 -0.0672 0.03825 0.02830 0.0083 1.0000 0.9820
-0.250 -0.0247 0.03811 0.02814 0.0026 1.0000 0.9938
0.000 0.0000 0.03808 0.02810 0.0000 1.0000 1.0000
0.250 0.0245 0.03810 0.02813 -0.0025 0.9938 1.0000
0.500 0.0671 0.03824 0.02829 -0.0083 0.9820 1.0000
0.750 0.1046 0.03841 0.02849 -0.0129 0.9697 1.0000
1.000 0.1385 0.03866 0.02878 -0.0167 0.9569 1.0000
1.250 0.1718 0.03899 0.02916 -0.0202 0.9434 1.0000
1.500 0.2040 0.03937 0.02961 -0.0233 0.9294 1.0000
1.750 0.2361 0.03981 0.03012 -0.0262 0.9144 1.0000
2.000 0.2676 0.04028 0.03067 -0.0287 0.8989 1.0000
2.250 0.3025 0.04076 0.03125 -0.0316 0.8824 1.0000
2.500 0.3439 0.04123 0.03185 -0.0352 0.8655 1.0000
2.750 0.3604 0.04177 0.03247 -0.0347 0.8473 1.0000
3.000 0.3828 0.04229 0.03309 -0.0350 0.8284 1.0000
3.250 0.4219 0.04265 0.03362 -0.0374 0.8093 1.0000
3.500 0.4643 0.04290 0.03403 -0.0400 0.7898 1.0000
3.750 0.4740 0.04345 0.03468 -0.0378 0.7693 1.0000
4.000 0.5298 0.04313 0.03460 -0.0412 0.7488 1.0000
4.250 0.5398 0.04351 0.03509 -0.0385 0.7278 1.0000
4.500 0.5674 0.04326 0.03500 -0.0375 0.7066 1.0000
4.750 0.6049 0.04239 0.03432 -0.0370 0.6863 1.0000
5.000 0.6102 0.04251 0.03456 -0.0332 0.6641 1.0000
5.250 0.6593 0.04028 0.03256 -0.0324 0.6444 1.0000
5.500 0.6615 0.04027 0.03266 -0.0281 0.6210 1.0000
5.750 0.7121 0.03700 0.02960 -0.0262 0.6006 1.0000
6.000 0.7249 0.03607 0.02882 -0.0222 0.5758 1.0000
6.250 0.7560 0.03375 0.02662 -0.0189 0.5499 1.0000
6.500 0.7861 0.03153 0.02443 -0.0155 0.5195 1.0000
6.750 0.8143 0.02977 0.02253 -0.0121 0.4842 1.0000
7.000 0.8264 0.02956 0.02222 -0.0083 0.4476 1.0000
7.250 0.8401 0.02959 0.02199 -0.0048 0.4103 1.0000
7.500 0.8464 0.03016 0.02239 -0.0011 0.3763 1.0000
7.750 0.8510 0.03093 0.02300 0.0027 0.3457 1.0000
8.000 0.8553 0.03177 0.02364 0.0065 0.3175 1.0000
8.250 0.8609 0.03274 0.02442 0.0100 0.2914 1.0000
8.500 0.8617 0.03393 0.02559 0.0138 0.2683 1.0000
8.750 0.8737 0.03534 0.02680 0.0160 0.2435 1.0000
9.000 0.8847 0.03689 0.02833 0.0181 0.2207 1.0000
9.250 0.9003 0.03885 0.03018 0.0195 0.2004 1.0000
9.500 0.9108 0.04089 0.03232 0.0213 0.1834 1.0000
9.750 0.9236 0.04325 0.03478 0.0227 0.1691 1.0000
10.000 0.9359 0.04563 0.03721 0.0240 0.1563 1.0000
10.250 0.9550 0.04840 0.03991 0.0246 0.1450 1.0000
10.500 0.9445 0.05152 0.04359 0.0275 0.1401 1.0000
10.750 0.9626 0.05425 0.04622 0.0280 0.1306 1.0000
11.000 0.9469 0.05788 0.05030 0.0306 0.1290 1.0000
11.250 0.9278 0.06160 0.05434 0.0330 0.1281 1.0000
11.500 0.9031 0.06547 0.05844 0.0350 0.1279 1.0000
11.750 0.8765 0.07003 0.06318 0.0356 0.1284 1.0000
12.000 0.8482 0.07539 0.06868 0.0350 0.1292 1.0000
12.250 0.8206 0.08158 0.07496 0.0332 0.1303 1.0000
12.500 0.7950 0.08859 0.08202 0.0305 0.1312 1.0000
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