EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.18 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1230-il-1000000.txt Download as CSV file: xf-e1230-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.5804 0.13644 0.13434 -0.0322 1.0000 0.0102
-17.000 -0.6934 0.10809 0.10562 -0.0467 1.0000 0.0099
-16.750 -0.7410 0.09519 0.09253 -0.0537 1.0000 0.0098
-16.500 -0.7762 0.08498 0.08216 -0.0593 1.0000 0.0097
-16.250 -0.8054 0.07614 0.07317 -0.0642 1.0000 0.0097
-16.000 -0.8290 0.06856 0.06544 -0.0685 1.0000 0.0096
-15.750 -0.8494 0.06204 0.05877 -0.0720 1.0000 0.0096
-15.500 -0.8665 0.05654 0.05314 -0.0747 1.0000 0.0096
-15.250 -0.8809 0.05188 0.04835 -0.0765 1.0000 0.0096
-15.000 -0.8931 0.04786 0.04422 -0.0776 1.0000 0.0096
-14.750 -0.9032 0.04440 0.04065 -0.0780 1.0000 0.0096
-14.500 -0.9119 0.04134 0.03748 -0.0780 1.0000 0.0097
-14.250 -0.9191 0.03864 0.03468 -0.0775 1.0000 0.0097
-14.000 -0.9246 0.03627 0.03221 -0.0766 1.0000 0.0097
-13.750 -0.9293 0.03410 0.02996 -0.0754 1.0000 0.0097
-13.500 -0.9334 0.03215 0.02791 -0.0740 1.0000 0.0098
-13.250 -0.9377 0.03041 0.02609 -0.0720 1.0000 0.0098
-13.000 -0.9431 0.02893 0.02452 -0.0694 1.0000 0.0099
-12.750 -0.9508 0.02774 0.02326 -0.0656 1.0000 0.0099
-12.500 -0.9634 0.02686 0.02231 -0.0603 1.0000 0.0099
-12.250 -0.9448 0.02579 0.02114 -0.0604 0.9980 0.0100
-12.000 -0.9156 0.02471 0.01997 -0.0622 0.9958 0.0100
-11.750 -0.8891 0.02313 0.01828 -0.0639 0.9937 0.0102
-11.500 -0.8663 0.02144 0.01649 -0.0648 0.9900 0.0105
-11.250 -0.8349 0.02042 0.01542 -0.0667 0.9879 0.0107
-11.000 -0.8002 0.01963 0.01460 -0.0689 0.9866 0.0110
-10.750 -0.7728 0.01892 0.01385 -0.0694 0.9824 0.0113
-10.500 -0.7390 0.01818 0.01307 -0.0711 0.9799 0.0116
-10.250 -0.7028 0.01744 0.01228 -0.0734 0.9782 0.0119
-10.000 -0.6785 0.01679 0.01159 -0.0730 0.9719 0.0121
-9.750 -0.6433 0.01614 0.01090 -0.0749 0.9689 0.0124
-9.500 -0.6229 0.01564 0.01035 -0.0735 0.9583 0.0126
-9.250 -0.6098 0.01492 0.00958 -0.0707 0.9399 0.0129
-9.000 -0.5711 0.01400 0.00863 -0.0733 0.9289 0.0135
-8.750 -0.5170 0.01328 0.00784 -0.0790 0.9125 0.0142
-8.500 -0.4793 0.01285 0.00723 -0.0811 0.8710 0.0148
-8.000 -0.4348 0.01239 0.00641 -0.0789 0.7987 0.0159
-7.500 -0.3901 0.01192 0.00572 -0.0767 0.7489 0.0177
-7.250 -0.3663 0.01175 0.00544 -0.0759 0.7282 0.0187
-7.000 -0.3437 0.01146 0.00508 -0.0748 0.7092 0.0204
-6.750 -0.3196 0.01130 0.00482 -0.0740 0.6910 0.0220
-6.500 -0.2963 0.01106 0.00453 -0.0731 0.6738 0.0248
-6.250 -0.2723 0.01083 0.00427 -0.0723 0.6582 0.0292
-6.000 -0.2485 0.01058 0.00402 -0.0715 0.6434 0.0371
-5.750 -0.2244 0.01037 0.00381 -0.0708 0.6292 0.0476
-5.500 -0.1999 0.01022 0.00364 -0.0701 0.6153 0.0573
-5.250 -0.1746 0.01007 0.00349 -0.0695 0.6022 0.0658
-5.000 -0.1492 0.00994 0.00334 -0.0689 0.5897 0.0740
-4.750 -0.1241 0.00984 0.00321 -0.0683 0.5769 0.0827
-4.500 -0.0983 0.00971 0.00308 -0.0679 0.5655 0.0925
-4.250 -0.0728 0.00960 0.00296 -0.0674 0.5549 0.1039
-4.000 -0.0472 0.00947 0.00284 -0.0668 0.5441 0.1177
-3.750 -0.0218 0.00933 0.00272 -0.0663 0.5340 0.1350
-3.500 0.0032 0.00919 0.00261 -0.0657 0.5232 0.1577
-3.250 0.0279 0.00896 0.00250 -0.0651 0.5139 0.1960
-3.000 0.0511 0.00866 0.00237 -0.0643 0.5043 0.2543
-2.750 0.0743 0.00830 0.00224 -0.0635 0.4962 0.3282
-2.500 0.0967 0.00790 0.00211 -0.0625 0.4875 0.4164
-2.250 0.1196 0.00758 0.00204 -0.0616 0.4794 0.5042
-2.000 0.1452 0.00748 0.00205 -0.0610 0.4708 0.5528
-1.750 0.1715 0.00749 0.00207 -0.0606 0.4622 0.5806
-1.500 0.1990 0.00752 0.00209 -0.0604 0.4542 0.5982
-1.250 0.2261 0.00761 0.00213 -0.0601 0.4458 0.6115
-1.000 0.2542 0.00766 0.00216 -0.0600 0.4395 0.6223
-0.750 0.2818 0.00775 0.00221 -0.0598 0.4320 0.6307
-0.500 0.3096 0.00786 0.00227 -0.0597 0.4250 0.6389
-0.250 0.3376 0.00795 0.00232 -0.0596 0.4182 0.6449
0.000 0.3649 0.00809 0.00239 -0.0594 0.4106 0.6510
0.250 0.3931 0.00821 0.00245 -0.0593 0.4050 0.6570
0.500 0.4206 0.00829 0.00252 -0.0592 0.3989 0.6633
0.750 0.4476 0.00845 0.00261 -0.0589 0.3922 0.6703
1.000 0.4753 0.00848 0.00264 -0.0588 0.3874 0.6760
1.250 0.5028 0.00855 0.00269 -0.0587 0.3817 0.6809
1.500 0.5299 0.00867 0.00276 -0.0585 0.3753 0.6850
1.750 0.5576 0.00874 0.00280 -0.0584 0.3704 0.6881
2.000 0.5855 0.00876 0.00282 -0.0584 0.3658 0.6911
2.250 0.6128 0.00884 0.00287 -0.0583 0.3607 0.6936
2.500 0.6396 0.00896 0.00295 -0.0581 0.3550 0.6961
2.750 0.6677 0.00901 0.00301 -0.0581 0.3516 0.6984
3.000 0.6953 0.00910 0.00307 -0.0581 0.3470 0.7006
3.250 0.7222 0.00922 0.00315 -0.0580 0.3420 0.7027
3.500 0.7488 0.00933 0.00323 -0.0578 0.3372 0.7055
3.750 0.7766 0.00937 0.00331 -0.0578 0.3342 0.7080
4.000 0.8038 0.00946 0.00339 -0.0577 0.3305 0.7103
4.250 0.8305 0.00958 0.00349 -0.0576 0.3265 0.7127
4.500 0.8564 0.00975 0.00362 -0.0573 0.3215 0.7153
4.750 0.8837 0.00984 0.00372 -0.0572 0.3186 0.7176
5.000 0.9109 0.00994 0.00382 -0.0572 0.3155 0.7196
5.250 0.9375 0.01003 0.00392 -0.0570 0.3122 0.7222
5.500 0.9634 0.01016 0.00406 -0.0568 0.3087 0.7250
5.750 0.9885 0.01035 0.00422 -0.0564 0.3045 0.7278
6.000 1.0151 0.01045 0.00435 -0.0562 0.3020 0.7306
6.250 1.0419 0.01055 0.00447 -0.0562 0.2994 0.7331
6.500 1.0681 0.01068 0.00461 -0.0560 0.2964 0.7354
6.750 1.0935 0.01082 0.00476 -0.0557 0.2933 0.7383
7.000 1.1180 0.01099 0.00494 -0.0552 0.2899 0.7416
7.250 1.1420 0.01120 0.00515 -0.0547 0.2865 0.7453
7.500 1.1681 0.01129 0.00530 -0.0545 0.2848 0.7491
7.750 1.1937 0.01140 0.00545 -0.0543 0.2825 0.7533
8.000 1.2180 0.01152 0.00562 -0.0538 0.2798 0.7588
8.250 1.2412 0.01167 0.00581 -0.0531 0.2769 0.7655
8.500 1.2631 0.01185 0.00604 -0.0522 0.2739 0.7787
8.750 1.2832 0.01201 0.00635 -0.0510 0.2704 0.8203
9.000 1.3222 0.01195 0.00666 -0.0536 0.2687 1.0000
9.250 1.3452 0.01211 0.00684 -0.0529 0.2665 1.0000
9.500 1.3675 0.01230 0.00705 -0.0521 0.2640 1.0000
9.750 1.3889 0.01253 0.00729 -0.0512 0.2612 1.0000
10.000 1.4087 0.01283 0.00758 -0.0500 0.2576 1.0000
10.250 1.4279 0.01317 0.00791 -0.0488 0.2541 1.0000
10.500 1.4512 0.01334 0.00813 -0.0483 0.2521 1.0000
10.750 1.4734 0.01355 0.00837 -0.0476 0.2496 1.0000
11.000 1.4942 0.01382 0.00866 -0.0467 0.2467 1.0000
11.250 1.5135 0.01415 0.00900 -0.0456 0.2434 1.0000
11.500 1.5296 0.01463 0.00946 -0.0441 0.2390 1.0000
11.750 1.5519 0.01485 0.00974 -0.0435 0.2369 1.0000
12.000 1.5730 0.01513 0.01006 -0.0428 0.2342 1.0000
12.250 1.5920 0.01549 0.01045 -0.0418 0.2309 1.0000
12.500 1.6088 0.01596 0.01092 -0.0406 0.2272 1.0000
12.750 1.6240 0.01652 0.01149 -0.0392 0.2233 1.0000
13.000 1.6444 0.01685 0.01188 -0.0385 0.2206 1.0000
13.250 1.6622 0.01731 0.01238 -0.0375 0.2172 1.0000
13.500 1.6773 0.01792 0.01301 -0.0363 0.2132 1.0000
13.750 1.6893 0.01872 0.01381 -0.0349 0.2088 1.0000
14.000 1.7075 0.01921 0.01437 -0.0341 0.2057 1.0000
14.250 1.7221 0.01993 0.01511 -0.0331 0.2012 1.0000
14.500 1.7320 0.02096 0.01614 -0.0317 0.1961 1.0000
14.750 1.7455 0.02181 0.01704 -0.0308 0.1919 1.0000
15.000 1.7569 0.02283 0.01809 -0.0298 0.1866 1.0000
15.250 1.7620 0.02435 0.01961 -0.0285 0.1806 1.0000
15.500 1.7731 0.02549 0.02080 -0.0277 0.1756 1.0000
15.750 1.7766 0.02726 0.02259 -0.0266 0.1692 1.0000
16.000 1.7811 0.02904 0.02440 -0.0258 0.1634 1.0000
16.250 1.7812 0.03126 0.02663 -0.0249 0.1565 1.0000
16.500 1.7800 0.03368 0.02908 -0.0241 0.1501 1.0000
16.750 1.7731 0.03672 0.03214 -0.0234 0.1427 1.0000
17.000 1.7667 0.03981 0.03528 -0.0229 0.1361 1.0000
17.250 1.7519 0.04385 0.03934 -0.0225 0.1292 1.0000
17.500 1.7409 0.04762 0.04316 -0.0223 0.1231 1.0000
17.750 1.7212 0.05244 0.04802 -0.0223 0.1174 1.0000
18.000 1.7063 0.05683 0.05248 -0.0225 0.1124 1.0000
18.250 1.6857 0.06202 0.05772 -0.0229 0.1077 1.0000
18.500 1.6643 0.06738 0.06315 -0.0235 0.1036 1.0000
18.750 1.6462 0.07246 0.06830 -0.0241 0.0995 1.0000
19.000 1.6224 0.07833 0.07423 -0.0251 0.0957 1.0000
19.250 1.6021 0.08385 0.07982 -0.0261 0.0922 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 1230 AIRFOIL (e1230-il)