EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.93 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1230-il-1000000-n5.txt Download as CSV file: xf-e1230-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1230 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.8246 0.09758 0.09463 -0.0532 1.0000 0.0068
-17.500 -0.8851 0.08357 0.08041 -0.0606 1.0000 0.0068
-17.250 -0.9342 0.07153 0.06815 -0.0673 1.0000 0.0067
-17.000 -0.9682 0.06246 0.05888 -0.0725 1.0000 0.0067
-16.750 -0.9917 0.05580 0.05208 -0.0759 1.0000 0.0067
-16.500 -1.0088 0.05066 0.04681 -0.0781 1.0000 0.0067
-16.250 -1.0220 0.04647 0.04250 -0.0794 1.0000 0.0067
-16.000 -1.0316 0.04300 0.03892 -0.0800 1.0000 0.0067
-15.750 -1.0392 0.04000 0.03582 -0.0800 1.0000 0.0068
-15.500 -1.0446 0.03741 0.03315 -0.0796 1.0000 0.0068
-15.250 -1.0487 0.03510 0.03076 -0.0789 1.0000 0.0068
-15.000 -1.0513 0.03304 0.02862 -0.0779 1.0000 0.0069
-14.750 -1.0531 0.03115 0.02665 -0.0768 1.0000 0.0069
-14.500 -1.0544 0.02944 0.02486 -0.0753 1.0000 0.0070
-14.250 -1.0560 0.02792 0.02328 -0.0734 1.0000 0.0070
-14.000 -1.0416 0.02649 0.02176 -0.0740 0.9988 0.0071
-13.750 -1.0205 0.02522 0.02041 -0.0753 0.9970 0.0072
-13.500 -0.9971 0.02410 0.01922 -0.0767 0.9953 0.0073
-13.250 -0.9739 0.02311 0.01817 -0.0777 0.9935 0.0074
-13.000 -0.9545 0.02227 0.01726 -0.0775 0.9907 0.0075
-12.750 -0.9309 0.02146 0.01640 -0.0779 0.9885 0.0076
-12.500 -0.9020 0.02066 0.01554 -0.0792 0.9868 0.0076
-12.250 -0.8804 0.01997 0.01480 -0.0788 0.9835 0.0077
-12.000 -0.8553 0.01917 0.01394 -0.0792 0.9804 0.0078
-11.750 -0.8255 0.01831 0.01304 -0.0806 0.9784 0.0080
-11.500 -0.8110 0.01773 0.01242 -0.0784 0.9718 0.0082
-11.250 -0.7966 0.01722 0.01187 -0.0762 0.9630 0.0083
-11.000 -0.7850 0.01675 0.01138 -0.0732 0.9470 0.0085
-10.750 -0.7470 0.01607 0.01066 -0.0757 0.9336 0.0087
-10.500 -0.6866 0.01523 0.00973 -0.0828 0.9097 0.0090
-10.250 -0.6580 0.01490 0.00914 -0.0831 0.8527 0.0092
-10.000 -0.6373 0.01469 0.00873 -0.0818 0.8119 0.0094
-9.750 -0.6159 0.01445 0.00835 -0.0807 0.7809 0.0096
-9.500 -0.5937 0.01422 0.00798 -0.0797 0.7554 0.0099
-9.250 -0.5711 0.01399 0.00764 -0.0787 0.7331 0.0100
-9.000 -0.5486 0.01369 0.00725 -0.0778 0.7123 0.0104
-8.750 -0.5257 0.01342 0.00689 -0.0770 0.6932 0.0108
-8.500 -0.5021 0.01318 0.00657 -0.0762 0.6756 0.0112
-8.250 -0.4781 0.01296 0.00627 -0.0755 0.6589 0.0116
-8.000 -0.4538 0.01275 0.00599 -0.0748 0.6435 0.0121
-7.750 -0.4292 0.01256 0.00572 -0.0742 0.6291 0.0126
-7.500 -0.4051 0.01235 0.00544 -0.0735 0.6146 0.0132
-7.250 -0.3804 0.01214 0.00518 -0.0728 0.6014 0.0140
-7.000 -0.3554 0.01195 0.00494 -0.0723 0.5896 0.0149
-6.750 -0.3305 0.01179 0.00472 -0.0717 0.5767 0.0158
-6.500 -0.3054 0.01160 0.00449 -0.0711 0.5645 0.0173
-6.250 -0.2802 0.01144 0.00428 -0.0705 0.5538 0.0192
-6.000 -0.2551 0.01127 0.00408 -0.0700 0.5422 0.0219
-5.250 -0.1793 0.01075 0.00352 -0.0683 0.5121 0.0376
-4.750 -0.1282 0.01048 0.00323 -0.0674 0.4925 0.0523
-4.250 -0.0764 0.01023 0.00299 -0.0665 0.4760 0.0687
-4.000 -0.0504 0.01013 0.00288 -0.0660 0.4676 0.0774
-3.750 -0.0243 0.01003 0.00278 -0.0656 0.4599 0.0865
-3.500 0.0019 0.00993 0.00268 -0.0652 0.4512 0.0965
-3.250 0.0276 0.00982 0.00259 -0.0648 0.4433 0.1124
-3.000 0.0534 0.00967 0.00250 -0.0644 0.4363 0.1336
-2.750 0.0790 0.00954 0.00242 -0.0639 0.4291 0.1569
-2.500 0.1049 0.00940 0.00234 -0.0635 0.4234 0.1827
-2.250 0.1307 0.00925 0.00226 -0.0631 0.4168 0.2149
-1.750 0.1811 0.00889 0.00213 -0.0621 0.4035 0.3029
-1.500 0.2062 0.00870 0.00206 -0.0616 0.3969 0.3557
-1.250 0.2306 0.00848 0.00201 -0.0610 0.3909 0.4204
-1.000 0.2559 0.00826 0.00197 -0.0605 0.3864 0.4831
-0.750 0.2819 0.00815 0.00198 -0.0601 0.3811 0.5306
-0.500 0.3084 0.00815 0.00202 -0.0597 0.3752 0.5594
-0.250 0.3357 0.00817 0.00206 -0.0595 0.3701 0.5791
0.000 0.3632 0.00821 0.00210 -0.0594 0.3646 0.5946
0.250 0.3906 0.00828 0.00215 -0.0592 0.3591 0.6082
0.500 0.4180 0.00836 0.00223 -0.0590 0.3544 0.6231
0.750 0.4458 0.00844 0.00232 -0.0589 0.3507 0.6355
1.000 0.4736 0.00854 0.00239 -0.0588 0.3462 0.6444
1.250 0.5011 0.00866 0.00247 -0.0587 0.3410 0.6510
1.500 0.5289 0.00878 0.00254 -0.0587 0.3364 0.6558
1.750 0.5568 0.00886 0.00259 -0.0586 0.3324 0.6583
2.000 0.5844 0.00893 0.00265 -0.0586 0.3283 0.6604
2.250 0.6118 0.00903 0.00272 -0.0585 0.3241 0.6625
2.500 0.6392 0.00914 0.00279 -0.0584 0.3202 0.6646
2.750 0.6670 0.00922 0.00286 -0.0584 0.3173 0.6666
3.000 0.6946 0.00931 0.00293 -0.0583 0.3135 0.6687
3.250 0.7218 0.00943 0.00301 -0.0582 0.3093 0.6705
3.500 0.7487 0.00956 0.00310 -0.0581 0.3052 0.6719
3.750 0.7759 0.00964 0.00319 -0.0580 0.3023 0.6736
4.000 0.8032 0.00971 0.00327 -0.0579 0.2998 0.6755
4.250 0.8303 0.00980 0.00336 -0.0578 0.2968 0.6774
4.500 0.8570 0.00991 0.00346 -0.0577 0.2933 0.6791
4.750 0.8834 0.01005 0.00358 -0.0575 0.2895 0.6807
5.000 0.9099 0.01018 0.00370 -0.0573 0.2862 0.6823
5.250 0.9368 0.01028 0.00381 -0.0572 0.2841 0.6840
5.500 0.9635 0.01039 0.00393 -0.0571 0.2816 0.6856
5.750 0.9899 0.01052 0.00405 -0.0569 0.2790 0.6870
6.000 1.0158 0.01065 0.00418 -0.0567 0.2760 0.6887
6.250 1.0412 0.01080 0.00434 -0.0563 0.2725 0.6903
6.500 1.0669 0.01094 0.00449 -0.0561 0.2698 0.6920
6.750 1.0929 0.01106 0.00463 -0.0559 0.2678 0.6937
7.000 1.1187 0.01118 0.00479 -0.0556 0.2656 0.6956
7.250 1.1440 0.01133 0.00495 -0.0553 0.2632 0.6975
7.500 1.1690 0.01149 0.00512 -0.0549 0.2607 0.6993
7.750 1.1933 0.01167 0.00531 -0.0545 0.2579 0.7009
8.000 1.2164 0.01187 0.00551 -0.0538 0.2547 0.7025
8.500 1.2642 0.01214 0.00587 -0.0527 0.2510 0.7069
8.750 1.2880 0.01231 0.00607 -0.0521 0.2489 0.7097
9.000 1.3116 0.01250 0.00629 -0.0516 0.2465 0.7126
9.250 1.3345 0.01273 0.00653 -0.0510 0.2437 0.7154
9.500 1.3567 0.01299 0.00680 -0.0502 0.2406 0.7182
10.000 1.4024 0.01341 0.00732 -0.0490 0.2355 0.7261
10.250 1.4245 0.01364 0.00758 -0.0483 0.2320 0.7316
10.500 1.4456 0.01393 0.00789 -0.0475 0.2284 0.7370
10.750 1.4653 0.01425 0.00824 -0.0465 0.2247 0.7439
11.250 1.5073 0.01471 0.00889 -0.0449 0.2191 0.7746
11.500 1.5287 0.01469 0.00932 -0.0441 0.2148 0.9896
11.750 1.5457 0.01514 0.00976 -0.0428 0.2103 1.0000
12.000 1.5645 0.01552 0.01017 -0.0418 0.2071 1.0000
12.250 1.5830 0.01592 0.01060 -0.0407 0.2034 1.0000
12.500 1.5993 0.01643 0.01111 -0.0395 0.1988 1.0000
12.750 1.6140 0.01704 0.01172 -0.0381 0.1940 1.0000
13.000 1.6307 0.01756 0.01227 -0.0370 0.1898 1.0000
13.250 1.6447 0.01824 0.01297 -0.0356 0.1846 1.0000
13.500 1.6570 0.01905 0.01378 -0.0342 0.1796 1.0000
13.750 1.6707 0.01980 0.01456 -0.0330 0.1744 1.0000
14.000 1.6796 0.02089 0.01565 -0.0315 0.1680 1.0000
14.250 1.6901 0.02193 0.01671 -0.0303 0.1621 1.0000
14.500 1.6948 0.02343 0.01819 -0.0288 0.1542 1.0000
14.750 1.7009 0.02492 0.01970 -0.0276 0.1465 1.0000
15.000 1.7017 0.02688 0.02166 -0.0262 0.1385 1.0000
15.250 1.7000 0.02917 0.02395 -0.0250 0.1298 1.0000
15.500 1.6980 0.03162 0.02641 -0.0241 0.1221 1.0000
15.750 1.6913 0.03460 0.02940 -0.0233 0.1151 1.0000
16.000 1.6858 0.03760 0.03244 -0.0227 0.1087 1.0000
16.250 1.6763 0.04110 0.03598 -0.0223 0.1032 1.0000
16.500 1.6678 0.04459 0.03952 -0.0220 0.0981 1.0000
16.750 1.6538 0.04879 0.04378 -0.0220 0.0937 1.0000
17.000 1.6439 0.05264 0.04769 -0.0220 0.0898 1.0000
17.250 1.6286 0.05717 0.05228 -0.0223 0.0859 1.0000
17.500 1.6123 0.06195 0.05713 -0.0227 0.0827 1.0000
17.750 1.5985 0.06649 0.06176 -0.0232 0.0796 1.0000
18.000 1.5807 0.07162 0.06695 -0.0239 0.0765 1.0000
18.250 1.5616 0.07699 0.07239 -0.0248 0.0736 1.0000
18.500 1.5466 0.08191 0.07739 -0.0257 0.0711 1.0000
18.750 1.5286 0.08729 0.08284 -0.0268 0.0683 1.0000
19.000 1.5089 0.09300 0.08862 -0.0281 0.0657 1.0000
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Polar data table (+)
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