EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 520 AIRFOIL (e520-il) Reynolds number: 100,000 Max Cl/Cd: 35.24 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e520-il-100000-n5.txt Download as CSV file: xf-e520-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7583 0.14826 0.14334 0.0127 1.0000 0.0249
-16.500 -0.7918 0.13374 0.12874 0.0047 1.0000 0.0246
-16.250 -0.8232 0.12103 0.11590 -0.0029 1.0000 0.0242
-16.000 -0.8475 0.11089 0.10559 -0.0091 1.0000 0.0238
-15.750 -0.8707 0.10161 0.09613 -0.0147 1.0000 0.0238
-15.500 -0.8882 0.09403 0.08835 -0.0191 1.0000 0.0237
-15.250 -0.9040 0.08717 0.08126 -0.0229 1.0000 0.0239
-15.000 -0.9179 0.08102 0.07487 -0.0261 1.0000 0.0244
-14.750 -0.9286 0.07568 0.06928 -0.0286 1.0000 0.0248
-14.500 -0.9357 0.07120 0.06468 -0.0302 1.0000 0.0255
-14.250 -0.9395 0.06749 0.06087 -0.0315 1.0000 0.0263
-14.000 -0.9429 0.06392 0.05719 -0.0325 1.0000 0.0271
-13.750 -0.9452 0.06059 0.05373 -0.0333 1.0000 0.0281
-13.500 -0.9464 0.05747 0.05046 -0.0339 1.0000 0.0293
-13.250 -0.9467 0.05451 0.04730 -0.0342 1.0000 0.0310
-13.000 -0.9439 0.05186 0.04441 -0.0342 1.0000 0.0325
-12.750 -0.9428 0.04923 0.04176 -0.0341 1.0000 0.0343
-12.500 -0.9401 0.04692 0.03939 -0.0340 1.0000 0.0360
-12.250 -0.9354 0.04480 0.03716 -0.0337 1.0000 0.0384
-12.000 -0.9284 0.04284 0.03501 -0.0333 1.0000 0.0414
-11.750 -0.9233 0.04078 0.03292 -0.0326 1.0000 0.0438
-11.500 -0.9179 0.03890 0.03101 -0.0321 1.0000 0.0468
-11.250 -0.9096 0.03724 0.02923 -0.0314 1.0000 0.0508
-11.000 -0.9025 0.03552 0.02744 -0.0306 1.0000 0.0549
-10.750 -0.8952 0.03392 0.02581 -0.0298 1.0000 0.0592
-10.500 -0.8846 0.03253 0.02431 -0.0289 1.0000 0.0651
-10.250 -0.8780 0.03098 0.02281 -0.0280 1.0000 0.0711
-10.000 -0.8674 0.02969 0.02147 -0.0270 1.0000 0.0787
-9.750 -0.8581 0.02841 0.02021 -0.0261 1.0000 0.0874
-9.500 -0.8484 0.02722 0.01906 -0.0250 1.0000 0.0970
-9.250 -0.8381 0.02615 0.01802 -0.0238 1.0000 0.1083
-9.000 -0.8287 0.02520 0.01709 -0.0224 1.0000 0.1212
-8.750 -0.8151 0.02430 0.01623 -0.0217 0.9757 0.1365
-8.500 -0.7900 0.02334 0.01526 -0.0230 0.9519 0.1586
-8.250 -0.7674 0.02241 0.01438 -0.0236 0.9364 0.1813
-7.750 -0.7286 0.02096 0.01297 -0.0228 0.9136 0.2312
-7.500 -0.7116 0.02032 0.01236 -0.0217 0.9046 0.2580
-7.250 -0.6945 0.01975 0.01184 -0.0205 0.8966 0.2857
-7.000 -0.6773 0.01923 0.01138 -0.0193 0.8891 0.3158
-6.750 -0.6592 0.01875 0.01097 -0.0180 0.8827 0.3469
-6.250 -0.6209 0.01798 0.01034 -0.0157 0.8708 0.4115
-6.000 -0.6001 0.01771 0.01014 -0.0145 0.8660 0.4438
-5.750 -0.5780 0.01754 0.01004 -0.0136 0.8609 0.4750
-5.500 -0.5549 0.01747 0.01003 -0.0126 0.8559 0.5042
-5.250 -0.5310 0.01749 0.01006 -0.0117 0.8517 0.5308
-5.000 -0.5064 0.01757 0.01010 -0.0110 0.8472 0.5547
-4.750 -0.4808 0.01772 0.01022 -0.0104 0.8426 0.5747
-4.500 -0.4553 0.01788 0.01033 -0.0096 0.8385 0.5924
-4.250 -0.4300 0.01805 0.01039 -0.0090 0.8347 0.6084
-4.000 -0.4047 0.01822 0.01050 -0.0085 0.8299 0.6227
-3.750 -0.3793 0.01839 0.01059 -0.0078 0.8257 0.6355
-3.500 -0.3543 0.01853 0.01064 -0.0071 0.8220 0.6476
-3.250 -0.3298 0.01865 0.01066 -0.0066 0.8175 0.6595
-3.000 -0.3034 0.01887 0.01084 -0.0061 0.8129 0.6686
-2.750 -0.2778 0.01901 0.01090 -0.0055 0.8089 0.6777
-2.500 -0.2538 0.01905 0.01083 -0.0049 0.8049 0.6882
-2.250 -0.2269 0.01926 0.01105 -0.0045 0.7997 0.6946
-2.000 -0.2028 0.01928 0.01099 -0.0039 0.7952 0.7039
-1.750 -0.1758 0.01942 0.01108 -0.0033 0.7916 0.7100
-1.500 -0.1523 0.01945 0.01108 -0.0030 0.7856 0.7187
-1.250 -0.1257 0.01956 0.01119 -0.0024 0.7809 0.7241
-1.000 -0.1014 0.01949 0.01103 -0.0019 0.7771 0.7326
-0.750 -0.0756 0.01964 0.01121 -0.0015 0.7709 0.7372
-0.500 -0.0505 0.01964 0.01119 -0.0010 0.7658 0.7438
-0.250 -0.0246 0.01960 0.01111 -0.0004 0.7619 0.7496
0.000 0.0000 0.01969 0.01125 0.0000 0.7547 0.7548
0.250 0.0247 0.01960 0.01111 0.0004 0.7496 0.7619
0.500 0.0505 0.01964 0.01119 0.0010 0.7438 0.7658
0.750 0.0756 0.01964 0.01121 0.0015 0.7372 0.7709
1.000 0.1015 0.01949 0.01103 0.0019 0.7326 0.7771
1.250 0.1258 0.01956 0.01119 0.0024 0.7242 0.7810
1.500 0.1523 0.01945 0.01108 0.0029 0.7187 0.7857
1.750 0.1759 0.01942 0.01109 0.0033 0.7102 0.7917
2.000 0.2028 0.01930 0.01101 0.0039 0.7041 0.7952
2.250 0.2270 0.01927 0.01106 0.0045 0.6947 0.7997
2.500 0.2539 0.01904 0.01083 0.0049 0.6882 0.8049
2.750 0.2779 0.01899 0.01088 0.0055 0.6775 0.8089
3.000 0.3034 0.01886 0.01083 0.0061 0.6682 0.8129
3.250 0.3299 0.01865 0.01065 0.0066 0.6594 0.8175
3.500 0.3544 0.01853 0.01064 0.0071 0.6476 0.8220
3.750 0.3795 0.01839 0.01059 0.0078 0.6356 0.8257
4.000 0.4048 0.01822 0.01050 0.0084 0.6228 0.8300
4.250 0.4302 0.01805 0.01039 0.0089 0.6085 0.8347
4.500 0.4555 0.01788 0.01033 0.0096 0.5925 0.8385
4.750 0.4810 0.01771 0.01022 0.0103 0.5747 0.8426
5.000 0.5066 0.01757 0.01010 0.0109 0.5546 0.8472
5.250 0.5312 0.01749 0.01006 0.0116 0.5309 0.8517
5.500 0.5552 0.01747 0.01002 0.0126 0.5041 0.8559
5.750 0.5783 0.01754 0.01004 0.0135 0.4749 0.8609
6.000 0.6004 0.01771 0.01014 0.0144 0.4437 0.8660
6.250 0.6212 0.01798 0.01034 0.0156 0.4114 0.8708
6.500 0.6407 0.01834 0.01062 0.0168 0.3789 0.8769
6.750 0.6596 0.01876 0.01097 0.0180 0.3465 0.8827
7.000 0.6777 0.01923 0.01138 0.0192 0.3154 0.8891
7.250 0.6949 0.01976 0.01184 0.0204 0.2852 0.8966
7.500 0.7120 0.02033 0.01237 0.0216 0.2573 0.9046
7.750 0.7291 0.02097 0.01297 0.0227 0.2312 0.9136
8.250 0.7680 0.02241 0.01438 0.0235 0.1814 0.9363
8.500 0.7907 0.02333 0.01526 0.0229 0.1584 0.9519
8.750 0.8159 0.02430 0.01623 0.0216 0.1364 0.9756
9.000 0.8295 0.02521 0.01709 0.0222 0.1210 1.0000
9.250 0.8390 0.02616 0.01803 0.0236 0.1081 1.0000
9.500 0.8494 0.02722 0.01907 0.0248 0.0970 1.0000
9.750 0.8592 0.02841 0.02021 0.0259 0.0872 1.0000
10.000 0.8686 0.02969 0.02147 0.0268 0.0786 1.0000
10.250 0.8792 0.03098 0.02281 0.0278 0.0709 1.0000
10.500 0.8856 0.03254 0.02430 0.0287 0.0647 1.0000
10.750 0.8965 0.03391 0.02581 0.0296 0.0591 1.0000
11.000 0.9035 0.03554 0.02745 0.0304 0.0546 1.0000
11.250 0.9110 0.03724 0.02923 0.0312 0.0507 1.0000
11.500 0.9191 0.03892 0.03102 0.0318 0.0465 1.0000
11.750 0.9246 0.04079 0.03293 0.0324 0.0437 1.0000
12.000 0.9299 0.04285 0.03504 0.0330 0.0411 1.0000
12.250 0.9368 0.04481 0.03718 0.0335 0.0382 1.0000
12.500 0.9412 0.04695 0.03942 0.0337 0.0358 1.0000
12.750 0.9440 0.04927 0.04179 0.0339 0.0341 1.0000
13.000 0.9459 0.05188 0.04443 0.0340 0.0325 1.0000
13.250 0.9482 0.05455 0.04735 0.0340 0.0308 1.0000
13.500 0.9486 0.05747 0.05046 0.0337 0.0294 1.0000
13.750 0.9468 0.06061 0.05375 0.0331 0.0280 1.0000
14.000 0.9446 0.06393 0.05720 0.0323 0.0270 1.0000
14.250 0.9412 0.06746 0.06082 0.0312 0.0262 1.0000
14.500 0.9376 0.07121 0.06468 0.0300 0.0255 1.0000
14.750 0.9309 0.07566 0.06925 0.0284 0.0248 1.0000
15.000 0.9195 0.08110 0.07495 0.0258 0.0243 1.0000
15.250 0.9059 0.08721 0.08131 0.0226 0.0240 1.0000
15.500 0.8899 0.09410 0.08842 0.0188 0.0237 1.0000
15.750 0.8707 0.10205 0.09659 0.0142 0.0237 1.0000
16.000 0.8468 0.11156 0.10628 0.0083 0.0237 1.0000
16.250 0.8226 0.12171 0.11659 0.0022 0.0241 1.0000
16.500 0.7918 0.13433 0.12934 -0.0053 0.0246 1.0000
16.750 0.7532 0.15051 0.14561 -0.0141 0.0249 1.0000
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Polar data table (+)
Polar graphs
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