E220 (11.48%) (e220-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 100,000 Max Cl/Cd: 52.75 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e220-il-100000.txt Download as CSV file: xf-e220-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E220 (11.48%)
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4433 0.11771 0.11316 -0.0110 1.0000 0.0905
-10.250 -0.4565 0.11472 0.11026 -0.0166 1.0000 0.0940
-10.000 -0.4766 0.11161 0.10729 -0.0237 1.0000 0.0947
-9.750 -0.4391 0.10595 0.10157 -0.0177 1.0000 0.0981
-9.500 -0.4308 0.10248 0.09814 -0.0185 1.0000 0.1018
-9.250 -0.4361 0.09887 0.09461 -0.0224 1.0000 0.1066
-9.000 -0.4689 0.09474 0.09068 -0.0335 1.0000 0.1085
-8.750 -0.4297 0.09074 0.08662 -0.0261 1.0000 0.1131
-8.500 -0.4279 0.08725 0.08321 -0.0287 1.0000 0.1191
-8.250 -0.4480 0.08269 0.07879 -0.0370 1.0000 0.1215
-8.000 -0.4381 0.07889 0.07507 -0.0365 1.0000 0.1268
-7.750 -0.3418 0.06670 0.06315 -0.0412 0.9854 0.1455
-7.500 -0.4629 0.07471 0.07101 -0.0368 0.9908 0.1324
-7.250 -0.4475 0.06941 0.06563 -0.0433 0.9797 0.1425
-7.000 -0.4336 0.06414 0.06020 -0.0501 0.9694 0.1546
-6.500 -0.3818 0.02961 0.02444 -0.0616 0.9321 0.0831
-6.250 -0.4096 0.03993 0.03364 -0.0566 0.9364 0.0656
-6.000 -0.3882 0.03577 0.02905 -0.0565 0.9300 0.0613
-5.750 -0.3739 0.03234 0.02483 -0.0539 0.9211 0.0576
-5.500 -0.3474 0.02967 0.02155 -0.0533 0.9155 0.0570
-5.250 -0.3258 0.02789 0.01952 -0.0523 0.9082 0.0587
-5.000 -0.2983 0.02655 0.01794 -0.0521 0.9025 0.0643
-4.750 -0.2717 0.02502 0.01607 -0.0513 0.8965 0.0683
-4.500 -0.2456 0.02352 0.01462 -0.0510 0.8905 0.0765
-4.250 -0.2179 0.02228 0.01335 -0.0507 0.8861 0.0914
-4.000 -0.1999 0.02135 0.01255 -0.0491 0.8791 0.1132
-3.750 -0.1811 0.02009 0.01167 -0.0473 0.8737 0.1721
-3.500 -0.1701 0.01877 0.01127 -0.0447 0.8678 0.3219
-3.250 -0.1591 0.01773 0.01129 -0.0416 0.8619 0.5362
-3.000 -0.0546 0.01717 0.01156 -0.0521 0.8626 0.8723
-2.750 0.0149 0.01797 0.01198 -0.0577 0.8602 0.9291
-2.500 0.0950 0.01826 0.01187 -0.0666 0.8582 0.9649
-2.250 0.1752 0.01789 0.01118 -0.0771 0.8553 0.9939
-2.000 0.2098 0.01775 0.01085 -0.0798 0.8492 1.0000
-1.750 0.2273 0.01785 0.01080 -0.0786 0.8436 1.0000
-1.500 0.2469 0.01809 0.01094 -0.0784 0.8370 1.0000
-1.250 0.2659 0.01828 0.01100 -0.0774 0.8312 1.0000
-1.000 0.2855 0.01855 0.01117 -0.0767 0.8255 1.0000
-0.750 0.3052 0.01887 0.01141 -0.0760 0.8190 1.0000
-0.500 0.3251 0.01906 0.01150 -0.0747 0.8142 1.0000
-0.250 0.3446 0.01955 0.01194 -0.0743 0.8070 1.0000
0.000 0.3648 0.01980 0.01212 -0.0731 0.8015 1.0000
0.250 0.3840 0.02026 0.01254 -0.0723 0.7949 1.0000
0.500 0.4037 0.02062 0.01285 -0.0712 0.7885 1.0000
0.750 0.4235 0.02099 0.01318 -0.0700 0.7825 1.0000
1.000 0.4421 0.02148 0.01365 -0.0689 0.7750 1.0000
1.250 0.4638 0.02166 0.01378 -0.0674 0.7700 1.0000
1.500 0.4803 0.02236 0.01449 -0.0664 0.7611 1.0000
1.750 0.5032 0.02245 0.01455 -0.0649 0.7562 1.0000
2.000 0.5187 0.02320 0.01533 -0.0637 0.7466 1.0000
2.250 0.5426 0.02321 0.01531 -0.0622 0.7416 1.0000
2.500 0.5577 0.02396 0.01610 -0.0609 0.7314 1.0000
2.750 0.5789 0.02418 0.01635 -0.0593 0.7243 1.0000
3.000 0.5982 0.02452 0.01672 -0.0578 0.7155 1.0000
3.250 0.6163 0.02497 0.01722 -0.0562 0.7064 1.0000
3.500 0.6408 0.02484 0.01710 -0.0547 0.6995 1.0000
3.750 0.6578 0.02535 0.01767 -0.0530 0.6888 1.0000
4.000 0.6859 0.02485 0.01721 -0.0514 0.6835 1.0000
4.250 0.7029 0.02527 0.01771 -0.0497 0.6716 1.0000
4.500 0.7226 0.02543 0.01795 -0.0480 0.6609 1.0000
4.750 0.7522 0.02467 0.01724 -0.0464 0.6547 1.0000
5.000 0.7715 0.02476 0.01743 -0.0446 0.6425 1.0000
5.250 0.7929 0.02464 0.01740 -0.0428 0.6308 1.0000
5.500 0.8176 0.02415 0.01700 -0.0410 0.6202 1.0000
5.750 0.8473 0.02314 0.01606 -0.0394 0.6113 1.0000
6.000 0.8707 0.02264 0.01565 -0.0376 0.5977 1.0000
6.250 0.8951 0.02201 0.01512 -0.0358 0.5836 1.0000
6.500 0.9205 0.02124 0.01444 -0.0340 0.5685 1.0000
6.750 0.9418 0.02078 0.01413 -0.0321 0.5489 1.0000
7.000 0.9656 0.02007 0.01351 -0.0302 0.5279 1.0000
7.250 0.9867 0.01961 0.01313 -0.0281 0.5009 1.0000
7.500 1.0069 0.01928 0.01278 -0.0259 0.4683 1.0000
7.750 1.0229 0.01939 0.01284 -0.0234 0.4268 1.0000
8.000 1.0346 0.01993 0.01318 -0.0206 0.3798 1.0000
8.250 1.0420 0.02087 0.01386 -0.0174 0.3321 1.0000
8.500 1.0455 0.02206 0.01477 -0.0139 0.2873 1.0000
8.750 1.0460 0.02339 0.01585 -0.0102 0.2470 1.0000
9.000 1.0439 0.02482 0.01700 -0.0063 0.2133 1.0000
9.250 1.0400 0.02628 0.01823 -0.0023 0.1846 1.0000
9.500 1.0350 0.02770 0.01953 0.0018 0.1605 1.0000
9.750 1.0314 0.02936 0.02103 0.0052 0.1389 1.0000
10.000 1.0305 0.03111 0.02265 0.0080 0.1198 1.0000
10.250 1.0326 0.03309 0.02441 0.0105 0.1029 1.0000
10.500 1.0377 0.03496 0.02625 0.0126 0.0885 1.0000
10.750 1.0496 0.03690 0.02808 0.0144 0.0767 1.0000
11.000 1.0641 0.03869 0.03001 0.0160 0.0689 1.0000
11.250 1.0822 0.04085 0.03223 0.0171 0.0619 1.0000
11.500 1.0967 0.04285 0.03437 0.0184 0.0571 1.0000
11.750 1.1270 0.04638 0.03797 0.0185 0.0528 1.0000
12.000 1.1275 0.04871 0.04066 0.0206 0.0509 1.0000
12.250 1.1262 0.05109 0.04332 0.0225 0.0485 1.0000
12.500 1.1274 0.05391 0.04642 0.0240 0.0471 1.0000
12.750 1.1256 0.05709 0.04984 0.0254 0.0460 1.0000
13.000 1.1191 0.06051 0.05351 0.0266 0.0455 1.0000
13.250 1.1092 0.06418 0.05742 0.0276 0.0450 1.0000
13.500 1.0944 0.06825 0.06177 0.0281 0.0450 1.0000
13.750 1.0785 0.07249 0.06623 0.0282 0.0448 1.0000
14.000 1.0636 0.07692 0.07082 0.0278 0.0442 1.0000
14.250 1.0140 0.08489 0.07926 0.0249 0.0465 1.0000
14.500 0.9780 0.09282 0.08744 0.0212 0.0477 1.0000
14.750 0.9443 0.10151 0.09628 0.0164 0.0490 1.0000
15.000 0.9094 0.11185 0.10675 0.0102 0.0502 1.0000
15.250 0.8802 0.12265 0.11760 0.0039 0.0518 1.0000
15.500 0.8604 0.13245 0.12740 -0.0011 0.0529 1.0000
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Polar data table (+)
Polar graphs
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