EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 68 AIRFOIL (e68-il) Reynolds number: 100,000 Max Cl/Cd: 56.84 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e68-il-100000.txt Download as CSV file: xf-e68-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 68 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3736 0.11266 0.10786 -0.0408 1.0000 0.1220
-9.750 -0.4005 0.11078 0.10611 -0.0416 1.0000 0.1265
-9.500 -0.4458 0.10936 0.10488 -0.0433 1.0000 0.1276
-9.250 -0.4229 0.10484 0.10034 -0.0397 1.0000 0.1292
-9.000 -0.4166 0.10234 0.09786 -0.0370 1.0000 0.1310
-8.750 -0.4204 0.10012 0.09569 -0.0350 1.0000 0.1330
-8.500 -0.4308 0.09788 0.09352 -0.0334 1.0000 0.1354
-8.250 -0.4489 0.09561 0.09134 -0.0322 1.0000 0.1380
-8.000 -0.4605 0.07533 0.07152 -0.0363 1.0000 0.0822
-7.500 -0.6223 0.06402 0.05956 -0.0460 1.0000 0.0704
-7.250 -0.6529 0.05228 0.04678 -0.0483 1.0000 0.0611
-7.000 -0.6440 0.04880 0.04296 -0.0476 1.0000 0.0596
-6.750 -0.6346 0.04462 0.03844 -0.0473 1.0000 0.0589
-6.500 -0.6215 0.04089 0.03426 -0.0471 1.0000 0.0584
-6.250 -0.6052 0.03763 0.03047 -0.0467 1.0000 0.0585
-6.000 -0.5799 0.03500 0.02718 -0.0474 0.9983 0.0597
-5.750 -0.5447 0.03247 0.02443 -0.0502 0.9940 0.0636
-5.500 -0.5100 0.03095 0.02265 -0.0521 0.9886 0.0687
-5.250 -0.4718 0.02915 0.02048 -0.0542 0.9843 0.0740
-5.000 -0.4399 0.02793 0.01920 -0.0554 0.9787 0.0842
-4.750 -0.4048 0.02680 0.01818 -0.0575 0.9736 0.1068
-4.500 -0.3717 0.02608 0.01750 -0.0592 0.9680 0.1386
-4.250 -0.3392 0.02557 0.01711 -0.0609 0.9619 0.1756
-4.000 -0.3030 0.02510 0.01675 -0.0631 0.9570 0.2177
-3.750 -0.2752 0.02459 0.01642 -0.0638 0.9501 0.2616
-3.500 -0.2374 0.02428 0.01636 -0.0662 0.9453 0.3216
-3.250 -0.2126 0.02399 0.01633 -0.0662 0.9378 0.3777
-3.000 -0.1777 0.02391 0.01648 -0.0678 0.9323 0.4461
-2.750 -0.1518 0.02390 0.01665 -0.0677 0.9251 0.5050
-2.500 -0.1203 0.02398 0.01687 -0.0683 0.9189 0.5640
-2.250 -0.0934 0.02411 0.01713 -0.0680 0.9122 0.6142
-2.000 -0.0664 0.02424 0.01736 -0.0675 0.9050 0.6611
-1.750 -0.0381 0.02445 0.01763 -0.0672 0.8989 0.7063
-1.500 -0.0172 0.02460 0.01784 -0.0655 0.8908 0.7469
-1.250 0.0115 0.02478 0.01805 -0.0648 0.8854 0.7880
-1.000 0.0253 0.02490 0.01821 -0.0618 0.8762 0.8266
-0.750 0.0530 0.02497 0.01829 -0.0606 0.8710 0.8707
-0.500 0.0687 0.02502 0.01837 -0.0580 0.8617 0.9180
-0.250 0.1395 0.02513 0.01839 -0.0660 0.8586 0.9697
0.000 0.1796 0.02529 0.01840 -0.0701 0.8499 1.0000
0.250 0.2196 0.02529 0.01824 -0.0732 0.8443 1.0000
0.500 0.2409 0.02560 0.01842 -0.0733 0.8346 1.0000
0.750 0.2837 0.02561 0.01831 -0.0763 0.8295 1.0000
1.000 0.3048 0.02600 0.01861 -0.0759 0.8197 1.0000
1.250 0.3479 0.02595 0.01847 -0.0787 0.8149 1.0000
1.500 0.3682 0.02638 0.01884 -0.0780 0.8047 1.0000
1.750 0.4121 0.02623 0.01863 -0.0807 0.8002 1.0000
2.000 0.4315 0.02670 0.01905 -0.0798 0.7897 1.0000
2.250 0.4766 0.02639 0.01873 -0.0824 0.7855 1.0000
2.500 0.4961 0.02685 0.01916 -0.0814 0.7748 1.0000
2.750 0.5428 0.02636 0.01868 -0.0841 0.7709 1.0000
3.000 0.5629 0.02676 0.01908 -0.0831 0.7600 1.0000
3.250 0.6123 0.02602 0.01836 -0.0859 0.7565 1.0000
3.500 0.6696 0.02506 0.01747 -0.0900 0.7543 1.0000
3.750 0.6856 0.02544 0.01787 -0.0880 0.7421 1.0000
4.000 0.7088 0.02561 0.01807 -0.0872 0.7315 1.0000
4.250 0.7624 0.02459 0.01714 -0.0904 0.7273 1.0000
4.500 0.7881 0.02459 0.01719 -0.0898 0.7166 1.0000
4.750 0.8427 0.02341 0.01609 -0.0931 0.7116 1.0000
5.000 0.8683 0.02335 0.01611 -0.0923 0.6997 1.0000
5.250 0.9025 0.02295 0.01578 -0.0927 0.6892 1.0000
5.500 0.9553 0.02184 0.01473 -0.0957 0.6810 1.0000
5.750 0.9840 0.02159 0.01458 -0.0952 0.6672 1.0000
6.000 1.0147 0.02127 0.01432 -0.0949 0.6529 1.0000
6.250 1.0463 0.02093 0.01403 -0.0948 0.6376 1.0000
6.500 1.0758 0.02067 0.01383 -0.0944 0.6208 1.0000
6.750 1.0962 0.02069 0.01392 -0.0925 0.6016 1.0000
7.000 1.1211 0.02056 0.01383 -0.0914 0.5814 1.0000
7.250 1.1451 0.02050 0.01377 -0.0900 0.5598 1.0000
7.500 1.1640 0.02058 0.01387 -0.0879 0.5358 1.0000
7.750 1.1800 0.02076 0.01409 -0.0854 0.5100 1.0000
8.000 1.1945 0.02102 0.01432 -0.0827 0.4824 1.0000
8.250 1.2057 0.02139 0.01464 -0.0795 0.4525 1.0000
8.500 1.2138 0.02189 0.01507 -0.0759 0.4213 1.0000
8.750 1.2183 0.02251 0.01559 -0.0718 0.3899 1.0000
9.000 1.2208 0.02332 0.01625 -0.0676 0.3576 1.0000
9.250 1.2221 0.02433 0.01711 -0.0635 0.3253 1.0000
9.500 1.2220 0.02551 0.01815 -0.0595 0.2929 1.0000
9.750 1.2214 0.02687 0.01936 -0.0557 0.2618 1.0000
10.000 1.2202 0.02841 0.02072 -0.0521 0.2325 1.0000
10.250 1.2183 0.03008 0.02223 -0.0488 0.2055 1.0000
10.500 1.2163 0.03190 0.02385 -0.0457 0.1816 1.0000
10.750 1.2147 0.03376 0.02567 -0.0430 0.1578 1.0000
11.000 1.2133 0.03584 0.02758 -0.0405 0.1382 1.0000
11.250 1.2130 0.03796 0.02968 -0.0382 0.1196 1.0000
11.500 1.2124 0.04026 0.03190 -0.0361 0.1036 1.0000
11.750 1.2132 0.04267 0.03427 -0.0342 0.0897 1.0000
12.000 1.2175 0.04508 0.03664 -0.0325 0.0780 1.0000
12.250 1.2255 0.04743 0.03901 -0.0311 0.0687 1.0000
12.500 1.2384 0.04967 0.04112 -0.0300 0.0616 1.0000
12.750 1.2517 0.05190 0.04358 -0.0289 0.0568 1.0000
13.000 1.2753 0.05410 0.04571 -0.0284 0.0527 1.0000
13.250 1.2931 0.05715 0.04902 -0.0277 0.0501 1.0000
13.500 1.2961 0.06002 0.05221 -0.0263 0.0482 1.0000
13.750 1.2985 0.06297 0.05543 -0.0252 0.0464 1.0000
14.000 1.2988 0.06600 0.05867 -0.0243 0.0448 1.0000
14.250 1.2985 0.06948 0.06237 -0.0235 0.0439 1.0000
14.500 1.2958 0.07333 0.06644 -0.0229 0.0433 1.0000
14.750 1.2888 0.07761 0.07096 -0.0225 0.0429 1.0000
15.000 1.2757 0.08232 0.07595 -0.0224 0.0428 1.0000
15.250 1.2582 0.08746 0.08137 -0.0229 0.0428 1.0000
15.500 1.2357 0.09327 0.08749 -0.0241 0.0430 1.0000
15.750 1.2077 0.10011 0.09466 -0.0265 0.0434 1.0000
16.000 1.1655 0.10974 0.10467 -0.0314 0.0444 1.0000
16.250 1.1109 0.12330 0.11858 -0.0400 0.0462 1.0000
16.500 1.0600 0.13903 0.13453 -0.0506 0.0483 1.0000
16.750 1.0257 0.15337 0.14891 -0.0597 0.0503 1.0000
17.000 1.0098 0.16374 0.15927 -0.0654 0.0513 1.0000
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Polar data table (+)
Polar graphs
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