EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 3.0/12 (eh3012-il) Reynolds number: 200,000 Max Cl/Cd: 64.1 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh3012-il-200000.txt Download as CSV file: xf-eh3012-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EH 3.0/12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4041 0.08918 0.08607 -0.0160 1.0000 0.0526
-8.500 -0.4190 0.08388 0.08084 -0.0234 1.0000 0.0542
-8.250 -0.4350 0.07958 0.07654 -0.0271 1.0000 0.0545
-8.000 -0.4593 0.07609 0.07290 -0.0293 1.0000 0.0551
-7.750 -0.4660 0.07057 0.06734 -0.0299 1.0000 0.0556
-7.500 -0.4509 0.06674 0.06368 -0.0293 1.0000 0.0567
-7.250 -0.4410 0.06409 0.06110 -0.0288 1.0000 0.0578
-7.000 -0.4134 0.05997 0.05688 -0.0334 0.9361 0.0598
-6.750 -0.3964 0.05615 0.05278 -0.0356 0.8813 0.0627
-6.500 -0.3980 0.05531 0.05102 -0.0332 0.8424 0.0670
-6.250 -0.3918 0.04873 0.04447 -0.0328 0.8187 0.0686
-6.000 -0.3781 0.04622 0.04184 -0.0315 0.7958 0.0697
-5.750 -0.3638 0.04399 0.03944 -0.0302 0.7763 0.0715
-5.500 -0.3613 0.03354 0.02784 -0.0259 0.7661 0.0471
-5.250 -0.3474 0.02808 0.02163 -0.0230 0.7529 0.0396
-5.000 -0.3283 0.02481 0.01769 -0.0208 0.7391 0.0389
-4.750 -0.3050 0.02365 0.01630 -0.0198 0.7245 0.0406
-4.500 -0.2807 0.02214 0.01443 -0.0187 0.7109 0.0422
-4.250 -0.2550 0.02059 0.01251 -0.0177 0.6980 0.0433
-4.000 -0.2286 0.01956 0.01117 -0.0169 0.6856 0.0448
-3.750 -0.2032 0.01828 0.00983 -0.0163 0.6742 0.0484
-3.500 -0.1771 0.01770 0.00913 -0.0157 0.6628 0.0526
-3.250 -0.1510 0.01675 0.00806 -0.0150 0.6514 0.0565
-3.000 -0.1258 0.01622 0.00752 -0.0143 0.6415 0.0638
-2.750 -0.1014 0.01556 0.00684 -0.0134 0.6318 0.0741
-2.500 -0.0770 0.01502 0.00631 -0.0125 0.6217 0.0925
-2.250 -0.0532 0.01460 0.00588 -0.0117 0.6132 0.1150
-2.000 -0.0283 0.01429 0.00561 -0.0110 0.6032 0.1376
-1.750 -0.0044 0.01394 0.00534 -0.0102 0.5948 0.1665
-1.250 0.0159 0.01116 0.00492 -0.0033 0.5800 0.7334
-1.000 0.0492 0.01144 0.00544 -0.0020 0.5709 0.8877
-0.750 0.0886 0.01194 0.00578 -0.0028 0.5621 0.9242
-0.500 0.1585 0.01258 0.00613 -0.0099 0.5520 0.9433
-0.250 0.2221 0.01296 0.00634 -0.0163 0.5415 0.9586
0.000 0.2828 0.01322 0.00639 -0.0224 0.5324 0.9727
0.250 0.3461 0.01323 0.00621 -0.0294 0.5224 0.9862
0.500 0.4066 0.01301 0.00587 -0.0362 0.5125 0.9980
0.750 0.4363 0.01298 0.00570 -0.0369 0.5057 1.0000
1.000 0.4587 0.01300 0.00569 -0.0362 0.4986 1.0000
1.250 0.4812 0.01303 0.00564 -0.0354 0.4923 1.0000
1.500 0.5037 0.01309 0.00564 -0.0347 0.4859 1.0000
1.750 0.5262 0.01312 0.00564 -0.0339 0.4791 1.0000
2.000 0.5489 0.01322 0.00562 -0.0331 0.4739 1.0000
2.250 0.5714 0.01327 0.00571 -0.0324 0.4669 1.0000
2.500 0.5940 0.01334 0.00571 -0.0316 0.4610 1.0000
2.750 0.6165 0.01345 0.00579 -0.0308 0.4549 1.0000
3.000 0.6390 0.01352 0.00586 -0.0300 0.4485 1.0000
3.250 0.6617 0.01366 0.00588 -0.0292 0.4434 1.0000
3.500 0.6839 0.01376 0.00606 -0.0284 0.4367 1.0000
3.750 0.7062 0.01388 0.00615 -0.0275 0.4312 1.0000
4.000 0.7285 0.01407 0.00631 -0.0266 0.4261 1.0000
4.250 0.7504 0.01423 0.00652 -0.0257 0.4200 1.0000
4.500 0.7727 0.01439 0.00662 -0.0248 0.4149 1.0000
4.750 0.7944 0.01460 0.00687 -0.0238 0.4093 1.0000
5.000 0.8160 0.01477 0.00707 -0.0228 0.4032 1.0000
5.250 0.8384 0.01498 0.00719 -0.0219 0.3983 1.0000
5.500 0.8594 0.01521 0.00752 -0.0208 0.3923 1.0000
5.750 0.8811 0.01536 0.00768 -0.0198 0.3862 1.0000
6.000 0.9025 0.01555 0.00786 -0.0187 0.3796 1.0000
6.250 0.9235 0.01563 0.00797 -0.0176 0.3716 1.0000
6.500 0.9442 0.01573 0.00807 -0.0164 0.3632 1.0000
6.750 0.9654 0.01585 0.00822 -0.0153 0.3558 1.0000
7.000 0.9871 0.01611 0.00848 -0.0143 0.3503 1.0000
7.250 1.0082 0.01633 0.00879 -0.0132 0.3437 1.0000
7.500 1.0304 0.01658 0.00901 -0.0123 0.3384 1.0000
7.750 1.0512 0.01686 0.00942 -0.0113 0.3323 1.0000
8.000 1.0726 0.01709 0.00969 -0.0103 0.3262 1.0000
8.250 1.0937 0.01735 0.00998 -0.0092 0.3196 1.0000
8.500 1.1142 0.01755 0.01027 -0.0081 0.3119 1.0000
8.750 1.1351 0.01784 0.01058 -0.0071 0.3057 1.0000
9.000 1.1552 0.01811 0.01098 -0.0060 0.2988 1.0000
9.250 1.1760 0.01842 0.01127 -0.0050 0.2925 1.0000
9.500 1.1942 0.01863 0.01164 -0.0036 0.2828 1.0000
9.750 1.2128 0.01892 0.01200 -0.0023 0.2741 1.0000
10.000 1.2312 0.01924 0.01235 -0.0011 0.2658 1.0000
10.250 1.2486 0.01958 0.01283 0.0003 0.2560 1.0000
10.500 1.2648 0.01996 0.01329 0.0018 0.2453 1.0000
10.750 1.2789 0.02041 0.01378 0.0035 0.2322 1.0000
11.000 1.2907 0.02098 0.01439 0.0054 0.2165 1.0000
11.250 1.2992 0.02172 0.01513 0.0076 0.1986 1.0000
11.500 1.2992 0.02272 0.01608 0.0109 0.1787 1.0000
11.750 1.2974 0.02393 0.01727 0.0140 0.1598 1.0000
12.000 1.2871 0.02594 0.01919 0.0168 0.1352 1.0000
12.250 1.2696 0.02903 0.02213 0.0185 0.1071 1.0000
12.500 1.2533 0.03262 0.02562 0.0192 0.0854 1.0000
12.750 1.2309 0.03724 0.03012 0.0190 0.0648 1.0000
13.000 1.2157 0.04143 0.03430 0.0186 0.0551 1.0000
13.250 1.2043 0.04536 0.03828 0.0180 0.0503 1.0000
13.500 1.1912 0.04963 0.04261 0.0172 0.0465 1.0000
13.750 1.1791 0.05391 0.04698 0.0163 0.0439 1.0000
14.000 1.1700 0.05791 0.05108 0.0154 0.0429 1.0000
14.250 1.1564 0.06264 0.05588 0.0141 0.0414 1.0000
14.500 1.1432 0.06752 0.06086 0.0126 0.0403 1.0000
14.750 1.1328 0.07219 0.06562 0.0111 0.0395 1.0000
15.000 1.1256 0.07648 0.07002 0.0097 0.0390 1.0000
15.250 1.1188 0.08080 0.07444 0.0084 0.0383 1.0000
15.500 1.1134 0.08495 0.07868 0.0070 0.0377 1.0000
15.750 1.1093 0.08893 0.08275 0.0057 0.0371 1.0000
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Polar data table (+)
Polar graphs
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