EPPLER 603 AIRFOIL (e603-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 603 AIRFOIL (e603-il) Reynolds number: 500,000 Max Cl/Cd: 103.6 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e603-il-500000.txt Download as CSV file: xf-e603-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 603 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3276 0.07616 0.07297 -0.0992 0.7946 0.0165
-14.250 -0.4257 0.08208 0.07954 -0.0926 0.9397 0.0164
-14.000 -0.4455 0.06735 0.06451 -0.1095 0.9184 0.0160
-13.750 -0.4648 0.05633 0.05288 -0.1225 0.8638 0.0159
-13.500 -0.4937 0.05132 0.04742 -0.1231 0.8198 0.0156
-13.250 -0.5127 0.04783 0.04363 -0.1225 0.7973 0.0156
-13.000 -0.5358 0.04390 0.03938 -0.1214 0.7825 0.0153
-12.750 -0.5559 0.04039 0.03554 -0.1196 0.7711 0.0152
-12.500 -0.5669 0.03769 0.03256 -0.1177 0.7611 0.0152
-12.250 -0.5748 0.03504 0.02960 -0.1157 0.7532 0.0151
-12.000 -0.5753 0.03301 0.02733 -0.1139 0.7457 0.0151
-11.750 -0.5721 0.03124 0.02531 -0.1121 0.7396 0.0153
-11.500 -0.5644 0.02968 0.02357 -0.1107 0.7339 0.0154
-11.250 -0.5547 0.02835 0.02205 -0.1092 0.7284 0.0157
-11.000 -0.5417 0.02710 0.02059 -0.1080 0.7235 0.0159
-10.750 -0.5271 0.02602 0.01936 -0.1069 0.7190 0.0162
-10.500 -0.5113 0.02504 0.01822 -0.1058 0.7146 0.0165
-10.250 -0.4939 0.02420 0.01723 -0.1049 0.7106 0.0167
-10.000 -0.4718 0.02305 0.01596 -0.1044 0.7071 0.0171
-9.750 -0.4519 0.02219 0.01507 -0.1037 0.7040 0.0174
-9.500 -0.4336 0.02148 0.01435 -0.1029 0.7007 0.0179
-9.250 -0.4153 0.02088 0.01371 -0.1020 0.6975 0.0184
-9.000 -0.3969 0.02032 0.01309 -0.1011 0.6945 0.0192
-8.750 -0.3781 0.01981 0.01248 -0.1001 0.6917 0.0200
-8.500 -0.3604 0.01920 0.01179 -0.0991 0.6888 0.0207
-8.250 -0.3450 0.01847 0.01110 -0.0978 0.6863 0.0216
-8.000 -0.3278 0.01795 0.01056 -0.0966 0.6835 0.0225
-7.750 -0.3105 0.01744 0.01002 -0.0954 0.6810 0.0236
-7.500 -0.2943 0.01692 0.00944 -0.0940 0.6786 0.0246
-7.250 -0.2815 0.01629 0.00881 -0.0922 0.6764 0.0263
-7.000 -0.2659 0.01592 0.00839 -0.0906 0.6741 0.0281
-6.750 -0.2544 0.01549 0.00793 -0.0884 0.6719 0.0306
-6.500 -0.2376 0.01515 0.00759 -0.0870 0.6701 0.0341
-6.250 -0.2208 0.01469 0.00717 -0.0857 0.6680 0.0394
-6.000 -0.2023 0.01428 0.00679 -0.0846 0.6658 0.0473
-5.750 -0.1834 0.01385 0.00643 -0.0836 0.6635 0.0608
-5.500 -0.1635 0.01344 0.00611 -0.0828 0.6616 0.0823
-5.250 -0.1430 0.01303 0.00583 -0.0821 0.6598 0.1113
-5.000 -0.1222 0.01259 0.00555 -0.0816 0.6580 0.1531
-4.750 -0.1021 0.01205 0.00527 -0.0811 0.6561 0.2177
-4.250 -0.0641 0.00993 0.00431 -0.0809 0.6525 0.4896
-4.000 -0.0388 0.00955 0.00449 -0.0808 0.6506 0.6315
-3.750 -0.0093 0.00974 0.00467 -0.0811 0.6488 0.6610
-3.500 0.0205 0.00997 0.00484 -0.0814 0.6470 0.6782
-3.250 0.0495 0.01033 0.00517 -0.0814 0.6451 0.6899
-3.000 0.0789 0.01057 0.00535 -0.0816 0.6433 0.6982
-2.750 0.1077 0.01087 0.00561 -0.0816 0.6416 0.7037
-2.500 0.1377 0.01110 0.00574 -0.0821 0.6399 0.7105
-2.250 0.1659 0.01141 0.00604 -0.0820 0.6382 0.7150
-2.000 0.1930 0.01177 0.00644 -0.0815 0.6365 0.7200
-1.750 0.2220 0.01207 0.00669 -0.0817 0.6347 0.7281
-1.500 0.2478 0.01243 0.00711 -0.0807 0.6329 0.7322
-1.250 0.2741 0.01285 0.00755 -0.0799 0.6310 0.7362
-1.000 0.3020 0.01308 0.00775 -0.0798 0.6291 0.7410
-0.750 0.3336 0.01304 0.00762 -0.0812 0.6272 0.7455
-0.500 0.3617 0.01300 0.00755 -0.0814 0.6256 0.7468
-0.250 0.3904 0.01304 0.00755 -0.0817 0.6238 0.7480
0.000 0.4191 0.01316 0.00763 -0.0821 0.6218 0.7491
0.250 0.4467 0.01315 0.00765 -0.0823 0.6202 0.7505
0.500 0.4745 0.01315 0.00765 -0.0825 0.6182 0.7518
0.750 0.5030 0.01313 0.00763 -0.0830 0.6161 0.7532
1.000 0.5318 0.01312 0.00761 -0.0835 0.6139 0.7548
1.250 0.5613 0.01310 0.00757 -0.0842 0.6119 0.7567
1.500 0.5916 0.01305 0.00749 -0.0851 0.6099 0.7584
1.750 0.6226 0.01303 0.00741 -0.0862 0.6080 0.7601
2.000 0.6541 0.01313 0.00745 -0.0874 0.6058 0.7618
2.250 0.6814 0.01306 0.00743 -0.0877 0.6037 0.7631
2.500 0.7084 0.01303 0.00744 -0.0878 0.6013 0.7641
2.750 0.7362 0.01300 0.00744 -0.0881 0.5987 0.7650
3.000 0.7645 0.01298 0.00744 -0.0885 0.5962 0.7660
3.250 0.7936 0.01297 0.00742 -0.0890 0.5938 0.7670
3.500 0.8231 0.01298 0.00740 -0.0896 0.5915 0.7681
3.750 0.8523 0.01309 0.00750 -0.0902 0.5888 0.7694
4.000 0.8785 0.01306 0.00755 -0.0902 0.5859 0.7709
4.250 0.9060 0.01302 0.00755 -0.0905 0.5826 0.7722
4.500 0.9347 0.01295 0.00749 -0.0910 0.5792 0.7734
4.750 0.9645 0.01289 0.00742 -0.0918 0.5760 0.7747
5.000 0.9943 0.01293 0.00743 -0.0925 0.5727 0.7759
5.250 1.0203 0.01288 0.00747 -0.0926 0.5687 0.7773
5.500 1.0482 0.01285 0.00746 -0.0930 0.5646 0.7786
5.750 1.0757 0.01275 0.00738 -0.0932 0.5608 0.7797
6.000 1.1042 0.01274 0.00735 -0.0936 0.5570 0.7807
6.250 1.1276 0.01269 0.00743 -0.0931 0.5522 0.7817
6.500 1.1530 0.01264 0.00742 -0.0929 0.5472 0.7827
6.750 1.1799 0.01262 0.00740 -0.0930 0.5427 0.7837
7.000 1.2035 0.01262 0.00750 -0.0926 0.5369 0.7849
7.250 1.2276 0.01261 0.00754 -0.0922 0.5307 0.7861
7.500 1.2520 0.01263 0.00758 -0.0918 0.5244 0.7876
7.750 1.2743 0.01265 0.00768 -0.0911 0.5163 0.7892
8.000 1.2968 0.01271 0.00775 -0.0905 0.5083 0.7905
8.250 1.3177 0.01278 0.00787 -0.0896 0.4984 0.7919
8.500 1.3375 0.01291 0.00802 -0.0885 0.4877 0.7932
8.750 1.3543 0.01308 0.00819 -0.0868 0.4761 0.7944
9.000 1.3655 0.01329 0.00838 -0.0841 0.4629 0.7957
9.250 1.3749 0.01362 0.00870 -0.0812 0.4486 0.7971
9.500 1.3825 0.01409 0.00915 -0.0781 0.4324 0.7986
9.750 1.3882 0.01468 0.00972 -0.0749 0.4152 0.8003
10.000 1.3923 0.01541 0.01042 -0.0716 0.3980 0.8020
10.250 1.3935 0.01632 0.01129 -0.0681 0.3799 0.8037
10.500 1.3923 0.01746 0.01239 -0.0647 0.3617 0.8055
10.750 1.3892 0.01886 0.01375 -0.0614 0.3436 0.8073
11.000 1.3851 0.02051 0.01534 -0.0584 0.3260 0.8090
11.250 1.3800 0.02241 0.01717 -0.0557 0.3076 0.8105
11.500 1.3758 0.02438 0.01910 -0.0533 0.2895 0.8120
11.750 1.3700 0.02654 0.02121 -0.0510 0.2711 0.8136
12.000 1.3644 0.02879 0.02341 -0.0488 0.2535 0.8154
12.250 1.3585 0.03115 0.02573 -0.0469 0.2363 0.8172
12.500 1.3549 0.03345 0.02798 -0.0452 0.2206 0.8190
12.750 1.3527 0.03573 0.03022 -0.0438 0.2056 0.8206
13.000 1.3520 0.03797 0.03242 -0.0426 0.1915 0.8223
13.250 1.3527 0.04018 0.03461 -0.0417 0.1791 0.8239
13.500 1.3540 0.04243 0.03683 -0.0409 0.1672 0.8255
13.750 1.3548 0.04477 0.03913 -0.0402 0.1552 0.8270
14.000 1.3557 0.04715 0.04148 -0.0395 0.1441 0.8285
14.250 1.3592 0.04930 0.04364 -0.0390 0.1333 0.8302
14.500 1.3616 0.05164 0.04599 -0.0385 0.1235 0.8319
14.750 1.3637 0.05405 0.04839 -0.0382 0.1144 0.8336
15.000 1.3655 0.05658 0.05091 -0.0379 0.1052 0.8354
15.250 1.3700 0.05888 0.05323 -0.0378 0.0974 0.8373
15.500 1.3712 0.06160 0.05594 -0.0377 0.0897 0.8393
15.750 1.3742 0.06415 0.05849 -0.0377 0.0822 0.8414
16.000 1.3774 0.06679 0.06116 -0.0378 0.0761 0.8434
16.250 1.3784 0.06964 0.06402 -0.0379 0.0696 0.8455
16.500 1.3817 0.07228 0.06673 -0.0381 0.0642 0.8477
16.750 1.3815 0.07542 0.06987 -0.0384 0.0585 0.8498
17.000 1.3845 0.07822 0.07273 -0.0388 0.0537 0.8521
17.250 1.3845 0.08146 0.07599 -0.0394 0.0487 0.8545
17.500 1.3845 0.08479 0.07935 -0.0400 0.0440 0.8569
17.750 1.3846 0.08817 0.08277 -0.0407 0.0395 0.8592
18.000 1.3808 0.09204 0.08667 -0.0416 0.0355 0.8615
18.250 1.3803 0.09554 0.09026 -0.0424 0.0320 0.8642
18.500 1.3754 0.09974 0.09450 -0.0435 0.0290 0.8668
18.750 1.3744 0.10346 0.09831 -0.0447 0.0266 0.8700
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