EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 521 AIRFOIL (e521-il) Reynolds number: 100,000 Max Cl/Cd: 43.06 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e521-il-100000.txt Download as CSV file: xf-e521-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 521 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6497 0.13791 0.13305 -0.0014 1.0000 0.0778
-13.750 -0.7630 0.09868 0.09387 -0.0252 1.0000 0.0511
-13.500 -0.7844 0.09056 0.08569 -0.0298 1.0000 0.0502
-13.250 -0.8104 0.08280 0.07782 -0.0344 1.0000 0.0494
-13.000 -0.8382 0.07593 0.07079 -0.0380 1.0000 0.0488
-12.750 -0.8625 0.07021 0.06489 -0.0402 1.0000 0.0482
-12.500 -0.8864 0.06514 0.05960 -0.0413 1.0000 0.0478
-12.250 -0.9082 0.06071 0.05494 -0.0412 1.0000 0.0477
-12.000 -0.9273 0.05689 0.05085 -0.0403 1.0000 0.0481
-11.750 -0.9434 0.05353 0.04720 -0.0386 1.0000 0.0486
-11.500 -0.9576 0.05076 0.04413 -0.0361 1.0000 0.0496
-11.250 -0.9697 0.04844 0.04145 -0.0328 1.0000 0.0506
-11.000 -0.9758 0.04529 0.03793 -0.0301 1.0000 0.0523
-10.750 -0.9625 0.04234 0.03498 -0.0295 1.0000 0.0556
-10.500 -0.9530 0.04012 0.03254 -0.0279 1.0000 0.0591
-10.250 -0.9480 0.03838 0.03037 -0.0254 1.0000 0.0630
-10.000 -0.9273 0.03553 0.02755 -0.0253 1.0000 0.0688
-9.750 -0.9146 0.03397 0.02569 -0.0236 1.0000 0.0750
-9.500 -0.8938 0.03186 0.02366 -0.0233 1.0000 0.0827
-9.250 -0.8755 0.03003 0.02169 -0.0222 1.0000 0.0918
-9.000 -0.8620 0.02888 0.02043 -0.0205 1.0000 0.1020
-8.750 -0.8462 0.02740 0.01907 -0.0191 1.0000 0.1142
-8.500 -0.8392 0.02636 0.01812 -0.0163 1.0000 0.1266
-8.250 -0.8389 0.02557 0.01740 -0.0123 1.0000 0.1386
-8.000 -0.8392 0.02482 0.01670 -0.0081 1.0000 0.1516
-7.750 -0.8381 0.02408 0.01597 -0.0041 1.0000 0.1676
-7.500 -0.8348 0.02331 0.01521 -0.0006 1.0000 0.1866
-7.250 -0.8302 0.02250 0.01457 0.0027 1.0000 0.2073
-7.000 -0.8237 0.02172 0.01389 0.0058 1.0000 0.2321
-6.750 -0.8159 0.02097 0.01327 0.0086 1.0000 0.2603
-6.500 -0.8071 0.02024 0.01271 0.0112 1.0000 0.2916
-6.250 -0.7969 0.01954 0.01217 0.0137 1.0000 0.3270
-6.000 -0.7857 0.01887 0.01171 0.0161 1.0000 0.3661
-5.750 -0.7734 0.01826 0.01128 0.0184 1.0000 0.4090
-5.500 -0.7602 0.01773 0.01098 0.0207 1.0000 0.4555
-5.250 -0.7460 0.01733 0.01082 0.0230 1.0000 0.5047
-5.000 -0.7308 0.01717 0.01089 0.0255 1.0000 0.5526
-4.750 -0.7145 0.01730 0.01117 0.0280 1.0000 0.5965
-4.500 -0.6978 0.01763 0.01156 0.0305 1.0000 0.6346
-4.250 -0.6779 0.01817 0.01206 0.0325 0.9991 0.6663
-4.000 -0.6464 0.01905 0.01285 0.0324 0.9943 0.6947
-3.750 -0.6167 0.01996 0.01370 0.0329 0.9896 0.7158
-3.500 -0.5866 0.02070 0.01432 0.0329 0.9843 0.7378
-3.250 -0.5555 0.02154 0.01507 0.0331 0.9796 0.7546
-3.000 -0.5279 0.02218 0.01563 0.0338 0.9740 0.7707
-2.750 -0.4937 0.02290 0.01626 0.0333 0.9690 0.7864
-2.500 -0.4677 0.02337 0.01664 0.0343 0.9632 0.8013
-2.250 -0.4356 0.02386 0.01705 0.0340 0.9574 0.8154
-2.000 -0.4005 0.02436 0.01746 0.0330 0.9520 0.8289
-1.750 -0.3720 0.02465 0.01768 0.0332 0.9453 0.8422
-1.500 -0.3276 0.02513 0.01808 0.0303 0.9401 0.8547
-1.250 -0.3028 0.02530 0.01819 0.0308 0.9325 0.8677
-1.000 -0.2375 0.02593 0.01875 0.0244 0.9280 0.8745
-0.750 -0.1933 0.02619 0.01896 0.0211 0.9216 0.8845
-0.500 -0.1341 0.02649 0.01922 0.0152 0.9155 0.8919
-0.250 -0.0604 0.02669 0.01938 0.0064 0.9113 0.8982
0.000 0.0001 0.02677 0.01946 0.0000 0.9041 0.9041
0.250 0.0604 0.02670 0.01938 -0.0064 0.8982 0.9114
0.500 0.1342 0.02650 0.01922 -0.0152 0.8920 0.9155
0.750 0.1926 0.02620 0.01897 -0.0210 0.8845 0.9216
1.000 0.2375 0.02593 0.01875 -0.0244 0.8745 0.9280
1.250 0.3028 0.02530 0.01819 -0.0309 0.8677 0.9325
1.500 0.3276 0.02514 0.01808 -0.0303 0.8547 0.9401
1.750 0.3722 0.02465 0.01768 -0.0332 0.8422 0.9453
2.000 0.4006 0.02435 0.01745 -0.0330 0.8288 0.9521
2.250 0.4358 0.02385 0.01704 -0.0340 0.8153 0.9574
2.500 0.4678 0.02335 0.01662 -0.0342 0.8011 0.9632
2.750 0.4935 0.02290 0.01626 -0.0333 0.7864 0.9690
3.000 0.5280 0.02218 0.01563 -0.0339 0.7707 0.9740
3.250 0.5556 0.02154 0.01506 -0.0331 0.7546 0.9796
3.500 0.5868 0.02070 0.01432 -0.0329 0.7378 0.9843
3.750 0.6168 0.01996 0.01370 -0.0329 0.7157 0.9896
4.000 0.6465 0.01905 0.01286 -0.0324 0.6947 0.9942
4.250 0.6779 0.01817 0.01206 -0.0325 0.6663 0.9990
4.500 0.6979 0.01763 0.01156 -0.0305 0.6348 1.0000
4.750 0.7146 0.01730 0.01117 -0.0280 0.5965 1.0000
5.000 0.7309 0.01717 0.01089 -0.0255 0.5527 1.0000
5.250 0.7462 0.01733 0.01082 -0.0231 0.5045 1.0000
5.500 0.7605 0.01773 0.01099 -0.0208 0.4555 1.0000
5.750 0.7736 0.01826 0.01128 -0.0185 0.4088 1.0000
6.000 0.7859 0.01887 0.01171 -0.0162 0.3660 1.0000
6.250 0.7970 0.01954 0.01217 -0.0138 0.3270 1.0000
6.500 0.8072 0.02024 0.01271 -0.0113 0.2915 1.0000
6.750 0.8161 0.02097 0.01327 -0.0086 0.2602 1.0000
7.000 0.8239 0.02172 0.01389 -0.0058 0.2322 1.0000
7.250 0.8302 0.02249 0.01457 -0.0027 0.2072 1.0000
7.500 0.8350 0.02331 0.01522 0.0005 0.1866 1.0000
7.750 0.8383 0.02408 0.01597 0.0041 0.1676 1.0000
8.000 0.8393 0.02482 0.01670 0.0081 0.1516 1.0000
8.250 0.8388 0.02555 0.01739 0.0123 0.1385 1.0000
8.500 0.8392 0.02636 0.01813 0.0163 0.1265 1.0000
8.750 0.8460 0.02739 0.01906 0.0191 0.1142 1.0000
9.000 0.8620 0.02888 0.02042 0.0205 0.1021 1.0000
9.250 0.8752 0.03002 0.02168 0.0223 0.0917 1.0000
9.500 0.8936 0.03185 0.02365 0.0233 0.0828 1.0000
9.750 0.9144 0.03394 0.02565 0.0237 0.0750 1.0000
10.000 0.9272 0.03553 0.02755 0.0253 0.0689 1.0000
10.250 0.9480 0.03839 0.03037 0.0254 0.0631 1.0000
10.500 0.9530 0.04014 0.03256 0.0279 0.0592 1.0000
10.750 0.9623 0.04232 0.03496 0.0295 0.0556 1.0000
11.000 0.9759 0.04536 0.03799 0.0301 0.0522 1.0000
11.250 0.9692 0.04834 0.04135 0.0329 0.0505 1.0000
11.500 0.9574 0.05070 0.04406 0.0361 0.0495 1.0000
11.750 0.9429 0.05358 0.04725 0.0387 0.0486 1.0000
12.000 0.9271 0.05690 0.05086 0.0403 0.0481 1.0000
12.250 0.9087 0.06073 0.05495 0.0412 0.0479 1.0000
12.500 0.8878 0.06503 0.05948 0.0412 0.0479 1.0000
12.750 0.8632 0.07017 0.06485 0.0402 0.0482 1.0000
13.000 0.8381 0.07600 0.07086 0.0380 0.0488 1.0000
13.250 0.8111 0.08282 0.07783 0.0344 0.0495 1.0000
13.500 0.7862 0.09042 0.08554 0.0300 0.0504 1.0000
13.750 0.7612 0.09910 0.09429 0.0248 0.0511 1.0000
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