EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 100,000 Max Cl/Cd: 30.63 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1213-il-100000.txt Download as CSV file: xf-e1213-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1213 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5288 0.15050 0.14485 0.0043 1.0000 0.1036
-14.500 -0.8540 0.07622 0.07027 -0.0382 1.0000 0.0947
-14.250 -0.9095 0.06464 0.05842 -0.0460 1.0000 0.0948
-14.000 -0.8783 0.06634 0.06038 -0.0436 1.0000 0.1022
-13.750 -0.9302 0.05611 0.04985 -0.0506 1.0000 0.1026
-13.500 -0.9092 0.05629 0.05029 -0.0493 1.0000 0.1103
-13.250 -0.9500 0.04881 0.04254 -0.0539 1.0000 0.1120
-13.000 -0.9850 0.04343 0.03684 -0.0557 1.0000 0.1143
-12.750 -0.9714 0.04318 0.03687 -0.0547 1.0000 0.1228
-12.500 -0.9703 0.04207 0.03584 -0.0534 1.0000 0.1297
-12.250 -0.9855 0.04014 0.03378 -0.0508 1.0000 0.1353
-12.000 -0.9636 0.04103 0.03488 -0.0492 1.0000 0.1439
-11.750 -0.4079 0.12289 0.11734 0.0003 1.0000 0.2161
-11.500 -0.4460 0.11990 0.11440 -0.0042 1.0000 0.2234
-11.250 -0.4696 0.10974 0.10422 -0.0096 1.0000 0.2074
-11.000 -0.4619 0.10507 0.09952 -0.0105 1.0000 0.2068
-10.750 -0.4623 0.10037 0.09483 -0.0119 1.0000 0.2091
-10.500 -0.4656 0.09535 0.08981 -0.0137 1.0000 0.2094
-10.250 -0.5038 0.08564 0.08011 -0.0195 1.0000 0.2068
-10.000 -0.7540 0.05074 0.04513 -0.0377 1.0000 0.2057
-9.250 -0.7539 0.04422 0.03827 -0.0335 1.0000 0.2224
-9.000 -0.7319 0.04379 0.03790 -0.0324 1.0000 0.2271
-8.750 -0.6902 0.04561 0.03992 -0.0314 1.0000 0.2320
-8.500 -0.7147 0.04098 0.03494 -0.0292 1.0000 0.2385
-8.250 -0.7141 0.03884 0.03267 -0.0270 1.0000 0.2434
-8.000 -0.6868 0.03960 0.03368 -0.0256 1.0000 0.2473
-7.750 -0.6970 0.03889 0.03300 -0.0213 1.0000 0.2506
-7.500 -0.6782 0.03550 0.02904 -0.0251 0.9835 0.2596
-7.250 -0.6165 0.03574 0.02954 -0.0300 0.9689 0.2657
-7.000 -0.5723 0.03345 0.02682 -0.0354 0.9504 0.2754
-6.750 -0.5253 0.03231 0.02568 -0.0390 0.9305 0.2816
-6.500 -0.4819 0.03155 0.02485 -0.0417 0.9083 0.2884
-6.250 -0.4575 0.02986 0.02261 -0.0425 0.8842 0.2960
-6.000 -0.4266 0.02926 0.02206 -0.0423 0.8620 0.3005
-5.750 -0.4018 0.02886 0.02157 -0.0413 0.8390 0.3057
-5.500 -0.3820 0.02805 0.02045 -0.0401 0.8182 0.3120
-5.250 -0.3610 0.02722 0.01938 -0.0390 0.7994 0.3170
-5.000 -0.3365 0.02687 0.01900 -0.0378 0.7815 0.3217
-4.750 -0.3134 0.02643 0.01840 -0.0367 0.7649 0.3275
-4.500 -0.2922 0.02583 0.01746 -0.0357 0.7483 0.3336
-4.250 -0.2678 0.02527 0.01690 -0.0348 0.7323 0.3381
-4.000 -0.2429 0.02497 0.01653 -0.0339 0.7177 0.3437
-3.750 -0.2187 0.02458 0.01589 -0.0329 0.7051 0.3500
-3.500 -0.1946 0.02409 0.01526 -0.0323 0.6901 0.3555
-3.250 -0.1689 0.02379 0.01497 -0.0316 0.6766 0.3609
-3.000 -0.1433 0.02352 0.01451 -0.0307 0.6654 0.3675
-2.750 -0.1184 0.02322 0.01404 -0.0302 0.6515 0.3739
-2.500 -0.0922 0.02289 0.01375 -0.0296 0.6397 0.3795
-2.250 -0.0662 0.02268 0.01344 -0.0289 0.6281 0.3866
-2.000 -0.0405 0.02250 0.01311 -0.0284 0.6161 0.3940
-1.750 -0.0136 0.02221 0.01281 -0.0277 0.6061 0.4004
-1.500 0.0122 0.02210 0.01268 -0.0273 0.5939 0.4084
-1.250 0.0392 0.02189 0.01232 -0.0267 0.5850 0.4166
-1.000 0.0650 0.02178 0.01232 -0.0262 0.5728 0.4252
-0.750 0.0921 0.02166 0.01202 -0.0257 0.5642 0.4348
-0.500 0.1180 0.02154 0.01205 -0.0252 0.5527 0.4444
-0.250 0.1451 0.02145 0.01184 -0.0246 0.5444 0.4563
0.000 0.1707 0.02140 0.01191 -0.0241 0.5334 0.4688
0.250 0.1980 0.02128 0.01173 -0.0235 0.5259 0.4826
0.500 0.2230 0.02127 0.01189 -0.0230 0.5149 0.4988
0.750 0.2501 0.02115 0.01174 -0.0223 0.5076 0.5190
1.000 0.2743 0.02118 0.01201 -0.0216 0.4973 0.5421
1.250 0.3007 0.02104 0.01192 -0.0208 0.4897 0.5733
1.500 0.3245 0.02104 0.01221 -0.0199 0.4807 0.6120
1.750 0.3494 0.02085 0.01228 -0.0187 0.4726 0.6679
2.000 0.3736 0.02074 0.01250 -0.0171 0.4653 0.7483
2.250 0.4097 0.02073 0.01287 -0.0173 0.4554 0.8586
2.500 0.4797 0.02107 0.01318 -0.0242 0.4445 0.9411
2.750 0.5500 0.02132 0.01326 -0.0318 0.4335 0.9862
3.000 0.5907 0.02170 0.01357 -0.0349 0.4244 1.0000
3.250 0.6080 0.02199 0.01377 -0.0334 0.4175 1.0000
3.500 0.6302 0.02225 0.01378 -0.0323 0.4124 1.0000
3.750 0.6463 0.02290 0.01453 -0.0308 0.4045 1.0000
4.000 0.6677 0.02322 0.01477 -0.0296 0.3981 1.0000
4.250 0.6920 0.02356 0.01489 -0.0288 0.3929 1.0000
4.500 0.7081 0.02431 0.01579 -0.0272 0.3851 1.0000
4.750 0.7307 0.02469 0.01609 -0.0262 0.3793 1.0000
5.000 0.7560 0.02510 0.01631 -0.0255 0.3747 1.0000
5.250 0.7705 0.02603 0.01744 -0.0239 0.3674 1.0000
5.500 0.7931 0.02645 0.01780 -0.0229 0.3617 1.0000
5.750 0.8204 0.02678 0.01792 -0.0224 0.3573 1.0000
6.000 0.8326 0.02797 0.01935 -0.0206 0.3507 1.0000
6.250 0.8531 0.02866 0.02006 -0.0196 0.3453 1.0000
6.500 0.8792 0.02902 0.02030 -0.0190 0.3411 1.0000
6.750 0.8955 0.03016 0.02153 -0.0177 0.3360 1.0000
7.000 0.9095 0.03132 0.02284 -0.0162 0.3302 1.0000
7.250 0.9330 0.03183 0.02329 -0.0155 0.3257 1.0000
7.500 0.9620 0.03220 0.02351 -0.0153 0.3222 1.0000
7.750 0.9641 0.03435 0.02597 -0.0130 0.3172 1.0000
8.000 0.9727 0.03600 0.02779 -0.0114 0.3124 1.0000
8.250 0.9954 0.03662 0.02839 -0.0107 0.3086 1.0000
8.500 1.0273 0.03677 0.02839 -0.0106 0.3053 1.0000
8.750 1.0184 0.03970 0.03162 -0.0080 0.3009 1.0000
9.000 0.9829 0.04439 0.03667 -0.0042 0.2963 1.0000
9.500 1.0158 0.04662 0.03893 -0.0024 0.2901 1.0000
9.750 1.0744 0.04524 0.03732 -0.0037 0.2875 1.0000
10.000 0.5053 0.11800 0.11095 -0.0300 0.3273 1.0000
10.250 0.5269 0.12052 0.11347 -0.0299 0.3244 1.0000
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Polar data table (+)
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