EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 341 AIRFOIL (e341-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.72 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e341-il-1000000-n5.txt Download as CSV file: xf-e341-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 341 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5621 0.07766 0.07497 -0.0137 0.6136 0.0049
-9.500 -0.6043 0.06787 0.06507 -0.0173 0.6127 0.0048
-9.000 -0.6586 0.05413 0.05095 -0.0129 0.6032 0.0047
-8.500 -0.7239 0.02994 0.02546 -0.0004 0.6006 0.0045
-8.250 -0.7119 0.02730 0.02247 0.0018 0.5905 0.0045
-8.000 -0.6967 0.02522 0.02006 0.0036 0.5800 0.0046
-7.750 -0.6809 0.02302 0.01751 0.0055 0.5692 0.0046
-7.500 -0.6614 0.02145 0.01567 0.0068 0.5585 0.0046
-7.250 -0.6395 0.02030 0.01431 0.0078 0.5477 0.0046
-7.000 -0.6170 0.01915 0.01296 0.0087 0.5381 0.0046
-6.750 -0.5935 0.01810 0.01172 0.0095 0.5294 0.0046
-6.500 -0.5695 0.01712 0.01056 0.0102 0.5202 0.0046
-6.250 -0.5449 0.01630 0.00959 0.0109 0.5121 0.0046
-6.000 -0.5201 0.01550 0.00866 0.0115 0.5031 0.0046
-5.750 -0.4951 0.01481 0.00784 0.0121 0.4945 0.0046
-5.500 -0.4701 0.01421 0.00712 0.0126 0.4854 0.0046
-5.250 -0.4452 0.01360 0.00643 0.0133 0.4779 0.0047
-5.000 -0.4200 0.01314 0.00588 0.0138 0.4703 0.0047
-4.750 -0.3948 0.01269 0.00537 0.0144 0.4638 0.0048
-4.500 -0.3693 0.01233 0.00495 0.0149 0.4567 0.0049
-4.250 -0.3436 0.01202 0.00458 0.0153 0.4495 0.0050
-4.000 -0.3177 0.01174 0.00426 0.0158 0.4427 0.0051
-3.750 -0.2917 0.01150 0.00397 0.0162 0.4355 0.0052
-3.500 -0.2654 0.01128 0.00371 0.0166 0.4301 0.0054
-3.250 -0.2392 0.01107 0.00347 0.0169 0.4241 0.0057
-2.750 -0.1862 0.01074 0.00305 0.0176 0.4137 0.0064
-2.500 -0.1597 0.01058 0.00286 0.0179 0.4079 0.0069
-2.250 -0.1333 0.01044 0.00269 0.0183 0.4021 0.0080
-2.000 -0.1065 0.01032 0.00255 0.0185 0.3974 0.0094
-1.750 -0.0798 0.01020 0.00242 0.0188 0.3925 0.0120
-1.500 -0.0535 0.01007 0.00231 0.0191 0.3879 0.0212
-1.250 -0.0270 0.00992 0.00221 0.0194 0.3842 0.0357
-1.000 -0.0011 0.00974 0.00213 0.0198 0.3802 0.0639
-0.750 0.0235 0.00947 0.00205 0.0203 0.3757 0.1235
-0.500 0.0357 0.00832 0.00184 0.0229 0.3718 0.4101
-0.250 0.0269 0.00655 0.00175 0.0304 0.3696 0.8463
0.000 0.0538 0.00671 0.00191 0.0309 0.3664 0.8738
0.250 0.0815 0.00687 0.00204 0.0311 0.3629 0.8834
0.500 0.1084 0.00707 0.00219 0.0316 0.3592 0.8937
0.750 0.1360 0.00729 0.00238 0.0319 0.3553 0.8989
1.000 0.1633 0.00746 0.00252 0.0322 0.3525 0.9046
1.250 0.1911 0.00755 0.00257 0.0323 0.3493 0.9079
1.500 0.2196 0.00758 0.00256 0.0321 0.3461 0.9087
1.750 0.2480 0.00763 0.00256 0.0320 0.3425 0.9093
2.000 0.2764 0.00769 0.00258 0.0318 0.3392 0.9099
2.250 0.3050 0.00773 0.00259 0.0316 0.3368 0.9106
2.500 0.3336 0.00777 0.00261 0.0314 0.3342 0.9111
2.750 0.3622 0.00782 0.00263 0.0312 0.3314 0.9116
3.000 0.3906 0.00788 0.00266 0.0309 0.3281 0.9121
3.250 0.4188 0.00796 0.00271 0.0307 0.3248 0.9128
3.500 0.4473 0.00801 0.00275 0.0305 0.3224 0.9135
3.750 0.4759 0.00806 0.00279 0.0302 0.3197 0.9141
4.000 0.5044 0.00812 0.00284 0.0300 0.3167 0.9146
4.250 0.5328 0.00818 0.00289 0.0297 0.3140 0.9151
4.500 0.5610 0.00827 0.00295 0.0295 0.3109 0.9157
4.750 0.5894 0.00835 0.00302 0.0292 0.3081 0.9163
5.000 0.6179 0.00840 0.00309 0.0289 0.3054 0.9168
5.250 0.6464 0.00847 0.00316 0.0285 0.3023 0.9173
5.500 0.6747 0.00856 0.00324 0.0282 0.2990 0.9179
5.750 0.7028 0.00867 0.00334 0.0279 0.2957 0.9186
6.000 0.7310 0.00876 0.00343 0.0276 0.2926 0.9193
6.250 0.7594 0.00884 0.00353 0.0273 0.2893 0.9198
6.500 0.7877 0.00894 0.00363 0.0269 0.2853 0.9203
6.750 0.8157 0.00907 0.00375 0.0266 0.2811 0.9208
7.000 0.8438 0.00918 0.00387 0.0263 0.2777 0.9213
7.250 0.8721 0.00928 0.00399 0.0259 0.2735 0.9217
7.500 0.8999 0.00943 0.00412 0.0256 0.2680 0.9221
7.750 0.9276 0.00957 0.00428 0.0252 0.2635 0.9225
8.000 0.9554 0.00970 0.00442 0.0249 0.2584 0.9230
8.250 0.9821 0.00988 0.00459 0.0248 0.2516 0.9236
8.500 1.0091 0.01003 0.00476 0.0246 0.2456 0.9241
8.750 1.0354 0.01025 0.00497 0.0244 0.2380 0.9247
9.000 1.0619 0.01044 0.00517 0.0243 0.2311 0.9253
9.250 1.0873 0.01072 0.00543 0.0242 0.2217 0.9259
9.500 1.1131 0.01097 0.00569 0.0242 0.2129 0.9265
9.750 1.1382 0.01127 0.00597 0.0242 0.2039 0.9271
10.000 1.1622 0.01165 0.00632 0.0243 0.1921 0.9279
10.250 1.1857 0.01205 0.00670 0.0244 0.1809 0.9288
10.500 1.2087 0.01250 0.00711 0.0246 0.1684 0.9297
10.750 1.2306 0.01304 0.00760 0.0249 0.1542 0.9305
11.000 1.2520 0.01358 0.00810 0.0252 0.1416 0.9314
11.250 1.2724 0.01419 0.00867 0.0257 0.1286 0.9323
11.750 1.3108 0.01549 0.00990 0.0267 0.1051 0.9343
12.000 1.3286 0.01620 0.01059 0.0273 0.0950 0.9353
12.250 1.3439 0.01694 0.01132 0.0282 0.0857 0.9364
12.500 1.3572 0.01778 0.01215 0.0292 0.0776 0.9376
12.750 1.3672 0.01878 0.01315 0.0305 0.0703 0.9392
13.000 1.3763 0.01989 0.01430 0.0316 0.0637 0.9409
13.250 1.3819 0.02144 0.01587 0.0322 0.0569 0.9429
13.500 1.3853 0.02349 0.01794 0.0322 0.0506 0.9451
13.750 1.3904 0.02566 0.02017 0.0316 0.0457 0.9474
14.000 1.3924 0.02834 0.02289 0.0307 0.0415 0.9496
14.500 1.3884 0.03445 0.02913 0.0291 0.0350 0.9534
14.750 1.3837 0.03768 0.03245 0.0285 0.0325 0.9557
15.000 1.3735 0.04159 0.03642 0.0278 0.0298 0.9581
15.250 1.3658 0.04527 0.04019 0.0270 0.0282 0.9603
15.500 1.3562 0.04924 0.04424 0.0260 0.0262 0.9623
15.750 1.3414 0.05315 0.04823 0.0261 0.0248 0.9652
16.000 1.3259 0.05714 0.05230 0.0262 0.0236 0.9687
16.500 1.2962 0.06438 0.05970 0.0277 0.0216 0.9847
16.750 1.2864 0.06861 0.06399 0.0266 0.0203 0.9908
17.000 1.2769 0.07281 0.06825 0.0255 0.0191 0.9952
17.250 1.2700 0.07684 0.07236 0.0240 0.0182 0.9980
17.500 1.2624 0.08113 0.07673 0.0223 0.0170 1.0000
17.750 1.2548 0.08543 0.08108 0.0207 0.0160 1.0000
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