EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 520 AIRFOIL (e520-il) Reynolds number: 200,000 Max Cl/Cd: 47.73 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e520-il-200000.txt Download as CSV file: xf-e520-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6917 0.17452 0.17099 0.0238 1.0000 0.0316
-16.500 -0.7837 0.13652 0.13307 0.0068 1.0000 0.0241
-16.250 -0.8375 0.11792 0.11430 -0.0047 1.0000 0.0227
-16.000 -0.8794 0.10406 0.10021 -0.0137 1.0000 0.0219
-15.750 -0.9174 0.09245 0.08830 -0.0210 1.0000 0.0212
-15.500 -0.9442 0.08388 0.07945 -0.0259 1.0000 0.0208
-15.250 -0.9629 0.07729 0.07264 -0.0292 1.0000 0.0207
-15.000 -0.9759 0.07207 0.06724 -0.0315 1.0000 0.0210
-14.750 -0.9871 0.06739 0.06237 -0.0333 1.0000 0.0212
-14.500 -0.9971 0.06307 0.05785 -0.0345 1.0000 0.0215
-14.250 -1.0043 0.05925 0.05385 -0.0353 1.0000 0.0220
-14.000 -1.0099 0.05571 0.05011 -0.0357 1.0000 0.0225
-13.750 -1.0135 0.05249 0.04669 -0.0358 1.0000 0.0232
-13.500 -1.0142 0.04961 0.04360 -0.0356 1.0000 0.0238
-13.250 -1.0160 0.04715 0.04088 -0.0353 1.0000 0.0248
-13.000 -1.0123 0.04400 0.03761 -0.0347 1.0000 0.0263
-12.750 -1.0068 0.04207 0.03568 -0.0343 1.0000 0.0278
-12.500 -1.0008 0.04023 0.03375 -0.0337 1.0000 0.0296
-12.250 -0.9936 0.03839 0.03174 -0.0330 1.0000 0.0316
-12.000 -0.9836 0.03624 0.02947 -0.0320 1.0000 0.0339
-11.750 -0.9754 0.03459 0.02784 -0.0313 1.0000 0.0365
-11.500 -0.9655 0.03315 0.02633 -0.0305 1.0000 0.0394
-11.250 -0.9539 0.03187 0.02488 -0.0297 1.0000 0.0420
-11.000 -0.9442 0.02999 0.02309 -0.0287 1.0000 0.0462
-10.750 -0.9324 0.02877 0.02179 -0.0279 1.0000 0.0502
-10.500 -0.9210 0.02731 0.02029 -0.0269 1.0000 0.0549
-10.250 -0.9104 0.02602 0.01904 -0.0260 1.0000 0.0603
-10.000 -0.8983 0.02474 0.01772 -0.0250 1.0000 0.0666
-9.750 -0.8869 0.02355 0.01658 -0.0242 1.0000 0.0747
-9.500 -0.8767 0.02231 0.01540 -0.0233 1.0000 0.0837
-9.250 -0.8668 0.02130 0.01443 -0.0222 1.0000 0.0945
-9.000 -0.8481 0.02024 0.01344 -0.0228 0.9785 0.1098
-8.750 -0.8198 0.01921 0.01240 -0.0246 0.9617 0.1318
-8.500 -0.7981 0.01824 0.01153 -0.0251 0.9479 0.1541
-8.250 -0.7798 0.01750 0.01084 -0.0245 0.9367 0.1779
-8.000 -0.7637 0.01689 0.01029 -0.0233 0.9269 0.2036
-7.750 -0.7486 0.01631 0.00979 -0.0218 0.9184 0.2310
-7.500 -0.7339 0.01577 0.00933 -0.0201 0.9109 0.2600
-7.250 -0.7176 0.01525 0.00890 -0.0187 0.9043 0.2913
-7.000 -0.7011 0.01476 0.00853 -0.0172 0.8983 0.3248
-6.750 -0.6836 0.01433 0.00820 -0.0158 0.8930 0.3605
-6.500 -0.6643 0.01393 0.00792 -0.0147 0.8873 0.3969
-6.250 -0.6447 0.01359 0.00770 -0.0134 0.8827 0.4334
-6.000 -0.6237 0.01333 0.00753 -0.0124 0.8785 0.4699
-5.750 -0.6009 0.01315 0.00746 -0.0116 0.8735 0.5040
-5.500 -0.5775 0.01308 0.00747 -0.0108 0.8692 0.5354
-5.250 -0.5534 0.01313 0.00755 -0.0099 0.8658 0.5624
-5.000 -0.5275 0.01324 0.00765 -0.0095 0.8614 0.5867
-4.750 -0.5011 0.01344 0.00785 -0.0091 0.8570 0.6056
-4.500 -0.4749 0.01368 0.00804 -0.0085 0.8534 0.6223
-4.250 -0.4489 0.01396 0.00827 -0.0078 0.8500 0.6367
-4.000 -0.4214 0.01424 0.00851 -0.0077 0.8454 0.6495
-3.750 -0.3948 0.01450 0.00872 -0.0073 0.8412 0.6613
-3.500 -0.3692 0.01472 0.00885 -0.0066 0.8375 0.6731
-3.250 -0.3410 0.01508 0.00922 -0.0063 0.8336 0.6804
-3.000 -0.3144 0.01528 0.00938 -0.0060 0.8287 0.6902
-2.750 -0.2875 0.01554 0.00961 -0.0054 0.8246 0.6980
-2.500 -0.2615 0.01572 0.00974 -0.0047 0.8212 0.7061
-2.250 -0.2345 0.01595 0.00997 -0.0046 0.8159 0.7141
-2.000 -0.2080 0.01610 0.01010 -0.0041 0.8113 0.7211
-1.750 -0.1818 0.01625 0.01021 -0.0034 0.8075 0.7281
-1.500 -0.1558 0.01637 0.01033 -0.0031 0.8024 0.7352
-1.250 -0.1291 0.01652 0.01048 -0.0026 0.7972 0.7411
-1.000 -0.1038 0.01652 0.01042 -0.0020 0.7931 0.7487
-0.750 -0.0774 0.01668 0.01062 -0.0015 0.7877 0.7537
-0.500 -0.0520 0.01667 0.01057 -0.0013 0.7820 0.7616
-0.250 -0.0257 0.01669 0.01059 -0.0004 0.7779 0.7658
0.000 0.0000 0.01678 0.01071 0.0000 0.7714 0.7714
0.250 0.0257 0.01669 0.01059 0.0004 0.7658 0.7779
0.500 0.0520 0.01667 0.01057 0.0012 0.7617 0.7820
0.750 0.0775 0.01669 0.01063 0.0015 0.7538 0.7877
1.000 0.1038 0.01653 0.01043 0.0020 0.7488 0.7931
1.250 0.1292 0.01654 0.01050 0.0026 0.7413 0.7973
1.500 0.1558 0.01638 0.01033 0.0031 0.7352 0.8024
1.750 0.1818 0.01624 0.01020 0.0034 0.7279 0.8075
2.000 0.2080 0.01608 0.01007 0.0041 0.7209 0.8113
2.250 0.2344 0.01594 0.00996 0.0046 0.7138 0.8159
2.500 0.2616 0.01572 0.00974 0.0047 0.7061 0.8212
2.750 0.2875 0.01554 0.00962 0.0054 0.6982 0.8246
3.000 0.3145 0.01529 0.00938 0.0060 0.6902 0.8287
3.250 0.3411 0.01508 0.00922 0.0062 0.6804 0.8336
3.500 0.3692 0.01472 0.00885 0.0066 0.6732 0.8375
3.750 0.3948 0.01450 0.00872 0.0073 0.6614 0.8412
4.000 0.4214 0.01424 0.00851 0.0077 0.6495 0.8454
4.250 0.4489 0.01396 0.00827 0.0078 0.6368 0.8500
4.500 0.4750 0.01368 0.00805 0.0085 0.6224 0.8534
4.750 0.5012 0.01344 0.00785 0.0090 0.6056 0.8571
5.000 0.5276 0.01324 0.00765 0.0095 0.5867 0.8614
5.250 0.5536 0.01313 0.00755 0.0098 0.5625 0.8658
5.500 0.5776 0.01308 0.00747 0.0107 0.5356 0.8692
5.750 0.6010 0.01315 0.00747 0.0116 0.5041 0.8735
6.000 0.6239 0.01334 0.00753 0.0123 0.4697 0.8785
6.250 0.6449 0.01359 0.00770 0.0134 0.4333 0.8827
6.500 0.6646 0.01393 0.00792 0.0146 0.3966 0.8872
6.750 0.6839 0.01433 0.00821 0.0157 0.3601 0.8930
7.000 0.7015 0.01476 0.00853 0.0171 0.3246 0.8982
7.250 0.7179 0.01526 0.00891 0.0186 0.2910 0.9042
7.500 0.7344 0.01578 0.00934 0.0200 0.2595 0.9109
7.750 0.7491 0.01631 0.00979 0.0217 0.2308 0.9184
8.000 0.7643 0.01690 0.01029 0.0232 0.2035 0.9269
8.250 0.7805 0.01751 0.01085 0.0244 0.1779 0.9366
8.500 0.7988 0.01824 0.01153 0.0250 0.1541 0.9478
8.750 0.8205 0.01922 0.01240 0.0245 0.1316 0.9615
9.000 0.8489 0.02024 0.01343 0.0226 0.1096 0.9783
9.250 0.8676 0.02130 0.01443 0.0220 0.0943 1.0000
9.500 0.8777 0.02232 0.01541 0.0231 0.0837 1.0000
9.750 0.8881 0.02355 0.01657 0.0240 0.0745 1.0000
10.000 0.8996 0.02474 0.01772 0.0248 0.0667 1.0000
10.250 0.9116 0.02600 0.01902 0.0258 0.0602 1.0000
10.500 0.9215 0.02737 0.02033 0.0267 0.0544 1.0000
10.750 0.9336 0.02876 0.02179 0.0277 0.0500 1.0000
11.000 0.9451 0.02997 0.02306 0.0284 0.0458 1.0000
11.250 0.9549 0.03185 0.02486 0.0295 0.0419 1.0000
11.500 0.9667 0.03317 0.02635 0.0303 0.0392 1.0000
11.750 0.9760 0.03457 0.02781 0.0311 0.0362 1.0000
12.000 0.9849 0.03643 0.02963 0.0319 0.0334 1.0000
12.250 0.9945 0.03841 0.03177 0.0328 0.0313 1.0000
12.500 1.0025 0.04026 0.03378 0.0335 0.0295 1.0000
12.750 1.0081 0.04207 0.03568 0.0340 0.0277 1.0000
13.000 1.0143 0.04405 0.03767 0.0345 0.0263 1.0000
13.250 1.0174 0.04724 0.04097 0.0351 0.0247 1.0000
13.500 1.0170 0.04964 0.04362 0.0354 0.0240 1.0000
13.750 1.0151 0.05253 0.04673 0.0355 0.0232 1.0000
14.000 1.0113 0.05579 0.05020 0.0354 0.0225 1.0000
14.250 1.0057 0.05931 0.05391 0.0350 0.0219 1.0000
14.500 0.9982 0.06321 0.05801 0.0342 0.0216 1.0000
14.750 0.9885 0.06751 0.06250 0.0330 0.0213 1.0000
15.000 0.9785 0.07195 0.06710 0.0313 0.0208 1.0000
15.250 0.9638 0.07750 0.07286 0.0288 0.0208 1.0000
15.500 0.9433 0.08441 0.08001 0.0254 0.0210 1.0000
15.750 0.9237 0.09160 0.08741 0.0212 0.0209 1.0000
16.000 0.8860 0.10307 0.09919 0.0141 0.0214 1.0000
16.250 0.8370 0.11850 0.11489 0.0040 0.0227 1.0000
16.500 0.7839 0.13697 0.13352 -0.0072 0.0242 1.0000
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Polar data table (+)
Polar graphs
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