EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 200,000 Max Cl/Cd: 60.89 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1230-il-200000-n5.txt Download as CSV file: xf-e1230-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6411 0.07274 0.06792 -0.0669 1.0000 0.0156
-13.750 -0.6722 0.06454 0.05946 -0.0719 1.0000 0.0155
-13.250 -0.7079 0.05470 0.04929 -0.0759 1.0000 0.0156
-13.000 -0.7206 0.05110 0.04555 -0.0763 1.0000 0.0156
-12.750 -0.7312 0.04801 0.04235 -0.0761 1.0000 0.0157
-12.500 -0.7402 0.04533 0.03957 -0.0754 1.0000 0.0157
-12.250 -0.7483 0.04297 0.03711 -0.0742 1.0000 0.0158
-12.000 -0.7562 0.04090 0.03494 -0.0725 1.0000 0.0159
-11.750 -0.7644 0.03914 0.03309 -0.0701 1.0000 0.0160
-11.500 -0.7737 0.03768 0.03155 -0.0667 1.0000 0.0161
-11.250 -0.7851 0.03651 0.03029 -0.0622 1.0000 0.0162
-11.000 -0.7931 0.03541 0.02912 -0.0578 1.0000 0.0164
-10.750 -0.7890 0.03411 0.02773 -0.0555 0.9990 0.0166
-10.500 -0.7605 0.03239 0.02583 -0.0577 0.9944 0.0170
-10.250 -0.7324 0.03076 0.02403 -0.0595 0.9888 0.0175
-10.000 -0.7039 0.02928 0.02237 -0.0611 0.9829 0.0181
-9.750 -0.6744 0.02793 0.02086 -0.0627 0.9769 0.0188
-9.250 -0.6256 0.02583 0.01869 -0.0633 0.9558 0.0202
-9.000 -0.6045 0.02484 0.01761 -0.0626 0.9410 0.0210
-8.750 -0.5792 0.02379 0.01643 -0.0626 0.9279 0.0218
-8.500 -0.5496 0.02270 0.01530 -0.0636 0.9162 0.0226
-8.250 -0.5155 0.02172 0.01426 -0.0654 0.9034 0.0237
-8.000 -0.4777 0.02075 0.01319 -0.0678 0.8891 0.0252
-7.750 -0.4375 0.01980 0.01214 -0.0707 0.8724 0.0270
-7.500 -0.3963 0.01900 0.01121 -0.0736 0.8524 0.0299
-7.250 -0.3600 0.01828 0.01040 -0.0756 0.8293 0.0332
-7.000 -0.3305 0.01770 0.00972 -0.0761 0.8048 0.0369
-6.750 -0.3044 0.01723 0.00914 -0.0759 0.7818 0.0417
-6.500 -0.2799 0.01685 0.00867 -0.0754 0.7602 0.0483
-6.250 -0.2564 0.01651 0.00824 -0.0746 0.7401 0.0561
-6.000 -0.2331 0.01622 0.00787 -0.0738 0.7216 0.0648
-5.750 -0.2098 0.01596 0.00753 -0.0729 0.7042 0.0741
-5.500 -0.1867 0.01571 0.00722 -0.0720 0.6877 0.0840
-5.250 -0.1636 0.01548 0.00692 -0.0711 0.6724 0.0948
-5.000 -0.1405 0.01525 0.00664 -0.0702 0.6574 0.1073
-4.750 -0.1175 0.01500 0.00638 -0.0693 0.6433 0.1222
-4.500 -0.0945 0.01476 0.00611 -0.0684 0.6303 0.1392
-4.250 -0.0716 0.01452 0.00586 -0.0675 0.6174 0.1591
-4.000 -0.0490 0.01423 0.00561 -0.0666 0.6048 0.1848
-3.750 -0.0268 0.01393 0.00537 -0.0656 0.5933 0.2203
-3.500 -0.0052 0.01357 0.00514 -0.0645 0.5818 0.2708
-3.250 0.0152 0.01313 0.00493 -0.0633 0.5711 0.3396
-3.000 0.0343 0.01270 0.00480 -0.0617 0.5606 0.4280
-2.750 0.0552 0.01248 0.00487 -0.0602 0.5506 0.5128
-2.500 0.0787 0.01253 0.00497 -0.0590 0.5408 0.5615
-2.250 0.1040 0.01262 0.00502 -0.0582 0.5309 0.5911
-2.000 0.1292 0.01277 0.00507 -0.0574 0.5214 0.6115
-1.750 0.1552 0.01289 0.00511 -0.0568 0.5121 0.6276
-1.500 0.1810 0.01305 0.00513 -0.0562 0.5036 0.6418
-1.250 0.2071 0.01317 0.00517 -0.0557 0.4953 0.6545
-1.000 0.2326 0.01329 0.00519 -0.0551 0.4868 0.6666
-0.750 0.2578 0.01340 0.00523 -0.0543 0.4788 0.6802
-0.500 0.2829 0.01347 0.00528 -0.0535 0.4706 0.6935
-0.250 0.3082 0.01358 0.00528 -0.0529 0.4636 0.7039
0.000 0.3347 0.01361 0.00531 -0.0525 0.4563 0.7103
0.250 0.3609 0.01369 0.00530 -0.0521 0.4494 0.7163
0.500 0.3872 0.01376 0.00529 -0.0518 0.4428 0.7210
0.750 0.4139 0.01381 0.00530 -0.0515 0.4356 0.7249
1.000 0.4400 0.01390 0.00530 -0.0512 0.4291 0.7291
1.250 0.4667 0.01399 0.00533 -0.0510 0.4231 0.7333
1.500 0.4934 0.01407 0.00537 -0.0508 0.4170 0.7368
1.750 0.5195 0.01417 0.00541 -0.0505 0.4115 0.7404
2.000 0.5459 0.01426 0.00548 -0.0503 0.4061 0.7443
2.250 0.5724 0.01436 0.00555 -0.0501 0.4001 0.7482
2.750 0.6242 0.01461 0.00572 -0.0495 0.3898 0.7558
3.000 0.6507 0.01470 0.00584 -0.0493 0.3848 0.7600
3.250 0.6768 0.01483 0.00597 -0.0490 0.3800 0.7642
3.750 0.7280 0.01514 0.00624 -0.0484 0.3711 0.7735
4.000 0.7540 0.01527 0.00641 -0.0481 0.3662 0.7794
4.500 0.8048 0.01560 0.00675 -0.0474 0.3577 0.7922
4.750 0.8303 0.01580 0.00695 -0.0471 0.3541 0.8003
5.000 0.8560 0.01594 0.00719 -0.0468 0.3501 0.8109
5.250 0.8814 0.01609 0.00743 -0.0465 0.3459 0.8266
5.750 0.9376 0.01650 0.00796 -0.0468 0.3382 0.9054
6.000 0.9793 0.01677 0.00832 -0.0500 0.3342 0.9566
6.250 1.0130 0.01705 0.00865 -0.0517 0.3303 1.0000
6.500 1.0351 0.01731 0.00890 -0.0509 0.3270 1.0000
6.750 1.0570 0.01760 0.00915 -0.0500 0.3237 1.0000
7.000 1.0790 0.01794 0.00943 -0.0492 0.3206 1.0000
7.250 1.1010 0.01821 0.00976 -0.0484 0.3174 1.0000
7.500 1.1230 0.01851 0.01010 -0.0476 0.3142 1.0000
7.750 1.1447 0.01882 0.01045 -0.0468 0.3111 1.0000
8.000 1.1660 0.01915 0.01078 -0.0459 0.3083 1.0000
8.250 1.1872 0.01950 0.01111 -0.0451 0.3055 1.0000
8.500 1.2084 0.01989 0.01149 -0.0442 0.3027 1.0000
8.750 1.2280 0.02022 0.01191 -0.0431 0.2997 1.0000
9.000 1.2472 0.02058 0.01234 -0.0419 0.2967 1.0000
9.250 1.2663 0.02097 0.01277 -0.0408 0.2939 1.0000
9.500 1.2853 0.02137 0.01320 -0.0396 0.2914 1.0000
9.750 1.3044 0.02179 0.01362 -0.0385 0.2888 1.0000
10.000 1.3237 0.02226 0.01409 -0.0375 0.2863 1.0000
10.250 1.3404 0.02272 0.01468 -0.0361 0.2834 1.0000
10.500 1.3573 0.02321 0.01526 -0.0348 0.2806 1.0000
10.750 1.3741 0.02372 0.01584 -0.0336 0.2779 1.0000
11.000 1.3905 0.02424 0.01642 -0.0323 0.2752 1.0000
11.250 1.4072 0.02478 0.01697 -0.0311 0.2726 1.0000
11.500 1.4244 0.02536 0.01756 -0.0300 0.2701 1.0000
11.750 1.4369 0.02605 0.01840 -0.0285 0.2672 1.0000
12.000 1.4492 0.02677 0.01924 -0.0270 0.2639 1.0000
12.250 1.4611 0.02751 0.02007 -0.0255 0.2607 1.0000
12.500 1.4737 0.02826 0.02086 -0.0242 0.2577 1.0000
12.750 1.4878 0.02901 0.02159 -0.0231 0.2548 1.0000
13.000 1.4960 0.03006 0.02282 -0.0217 0.2517 1.0000
13.250 1.5040 0.03119 0.02409 -0.0203 0.2482 1.0000
13.500 1.5119 0.03236 0.02536 -0.0192 0.2448 1.0000
13.750 1.5207 0.03351 0.02655 -0.0181 0.2415 1.0000
14.000 1.5298 0.03469 0.02776 -0.0172 0.2384 1.0000
14.250 1.5321 0.03648 0.02975 -0.0162 0.2346 1.0000
14.500 1.5349 0.03831 0.03171 -0.0154 0.2307 1.0000
14.750 1.5386 0.04009 0.03355 -0.0148 0.2270 1.0000
15.000 1.5442 0.04172 0.03518 -0.0142 0.2236 1.0000
15.250 1.5414 0.04435 0.03802 -0.0138 0.2197 1.0000
15.500 1.5390 0.04700 0.04081 -0.0136 0.2155 1.0000
15.750 1.5377 0.04955 0.04344 -0.0135 0.2115 1.0000
16.000 1.5358 0.05227 0.04621 -0.0135 0.2077 1.0000
16.250 1.5266 0.05601 0.05015 -0.0139 0.2031 1.0000
16.500 1.5192 0.05959 0.05381 -0.0143 0.1986 1.0000
16.750 1.5155 0.06270 0.05694 -0.0146 0.1944 1.0000
17.000 1.4990 0.06774 0.06218 -0.0157 0.1897 1.0000
17.250 1.4849 0.07249 0.06703 -0.0167 0.1847 1.0000
17.500 1.4775 0.07632 0.07088 -0.0175 0.1802 1.0000
17.750 1.4542 0.08262 0.07736 -0.0192 0.1750 1.0000
18.000 1.4381 0.08792 0.08274 -0.0206 0.1697 1.0000
18.250 1.4227 0.09318 0.08806 -0.0221 0.1647 1.0000
18.500 1.3974 0.10007 0.09509 -0.0243 0.1589 1.0000
18.750 1.3922 0.10390 0.09888 -0.0255 0.1536 1.0000
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