E195 (11.82%) (e195-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E195 (11.82%) (e195-il) Reynolds number: 100,000 Max Cl/Cd: 55.88 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e195-il-100000.txt Download as CSV file: xf-e195-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E195 (11.82%)
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3548 0.10567 0.10076 -0.0354 1.0000 0.1109
-9.500 -0.3714 0.10322 0.09843 -0.0395 1.0000 0.1158
-9.250 -0.4068 0.10112 0.09653 -0.0459 1.0000 0.1168
-9.000 -0.3581 0.09573 0.09102 -0.0388 1.0000 0.1206
-8.750 -0.3530 0.09294 0.08828 -0.0386 1.0000 0.1245
-8.500 -0.2854 0.08075 0.07662 -0.0403 1.0000 0.1345
-8.250 -0.2841 0.07813 0.07408 -0.0389 1.0000 0.1381
-8.000 -0.3000 0.07624 0.07233 -0.0373 1.0000 0.1416
-7.750 -0.3324 0.07692 0.07321 -0.0318 1.0000 0.1422
-7.500 -0.3810 0.07562 0.07207 -0.0350 0.9942 0.1449
-7.250 -0.3519 0.06998 0.06641 -0.0358 0.9895 0.1487
-7.000 -0.4820 0.07849 0.07471 -0.0343 0.9977 0.1447
-6.750 -0.4545 0.07355 0.06978 -0.0365 0.9915 0.1491
-6.500 -0.4326 0.06711 0.06318 -0.0478 0.9794 0.1621
-6.250 -0.4224 0.04614 0.04090 -0.0636 0.9654 0.0793
-6.000 -0.3933 0.03762 0.03081 -0.0672 0.9574 0.0629
-5.750 -0.3652 0.03444 0.02713 -0.0684 0.9474 0.0629
-5.500 -0.3296 0.03106 0.02342 -0.0711 0.9414 0.0648
-5.250 -0.2968 0.02867 0.02062 -0.0723 0.9327 0.0653
-5.000 -0.2524 0.02631 0.01792 -0.0753 0.9286 0.0672
-4.750 -0.2217 0.02479 0.01619 -0.0757 0.9191 0.0704
-4.500 -0.1784 0.02301 0.01425 -0.0784 0.9147 0.0777
-4.250 -0.1496 0.02191 0.01316 -0.0785 0.9054 0.0903
-4.000 -0.1135 0.02016 0.01163 -0.0799 0.9001 0.1311
-3.750 -0.0917 0.01892 0.01097 -0.0793 0.8903 0.2228
-3.500 -0.0601 0.01785 0.01059 -0.0804 0.8847 0.3647
-3.250 -0.0403 0.01752 0.01061 -0.0788 0.8747 0.4676
-3.000 -0.0088 0.01711 0.01040 -0.0787 0.8694 0.5612
-2.750 0.0101 0.01706 0.01050 -0.0766 0.8595 0.6268
-2.500 0.0400 0.01678 0.01035 -0.0758 0.8544 0.6958
-2.250 0.0585 0.01683 0.01049 -0.0733 0.8449 0.7528
-2.000 0.0893 0.01664 0.01035 -0.0723 0.8400 0.8165
-1.750 0.1196 0.01678 0.01051 -0.0718 0.8318 0.8774
-1.500 0.1817 0.01674 0.01028 -0.0772 0.8276 0.9316
-1.250 0.2605 0.01654 0.00981 -0.0863 0.8245 0.9686
-1.000 0.3417 0.01632 0.00936 -0.0976 0.8179 0.9998
-0.750 0.3557 0.01634 0.00923 -0.0960 0.8104 1.0000
-0.500 0.3658 0.01669 0.00948 -0.0939 0.8008 1.0000
-0.250 0.3873 0.01678 0.00941 -0.0929 0.7949 1.0000
0.000 0.4011 0.01726 0.00981 -0.0911 0.7856 1.0000
0.250 0.4256 0.01738 0.00980 -0.0904 0.7801 1.0000
0.500 0.4409 0.01792 0.01028 -0.0887 0.7712 1.0000
0.750 0.4661 0.01808 0.01033 -0.0881 0.7658 1.0000
1.000 0.4823 0.01866 0.01088 -0.0866 0.7573 1.0000
1.250 0.5077 0.01886 0.01100 -0.0860 0.7517 1.0000
1.500 0.5254 0.01946 0.01157 -0.0847 0.7439 1.0000
1.750 0.5502 0.01971 0.01178 -0.0841 0.7379 1.0000
2.000 0.5704 0.02025 0.01229 -0.0830 0.7309 1.0000
2.250 0.5931 0.02064 0.01267 -0.0822 0.7241 1.0000
2.500 0.6188 0.02093 0.01295 -0.0817 0.7186 1.0000
2.750 0.6367 0.02160 0.01365 -0.0805 0.7102 1.0000
3.000 0.6669 0.02166 0.01367 -0.0804 0.7057 1.0000
3.250 0.6812 0.02256 0.01464 -0.0789 0.6962 1.0000
3.500 0.7119 0.02257 0.01465 -0.0788 0.6914 1.0000
3.750 0.7267 0.02345 0.01561 -0.0773 0.6817 1.0000
4.000 0.7583 0.02337 0.01553 -0.0772 0.6767 1.0000
4.250 0.7734 0.02424 0.01651 -0.0757 0.6667 1.0000
4.500 0.8068 0.02400 0.01628 -0.0757 0.6615 1.0000
4.750 0.8224 0.02477 0.01716 -0.0742 0.6508 1.0000
5.000 0.8522 0.02468 0.01710 -0.0738 0.6439 1.0000
5.250 0.8753 0.02492 0.01745 -0.0727 0.6342 1.0000
5.500 0.8967 0.02524 0.01788 -0.0715 0.6241 1.0000
5.750 0.9328 0.02458 0.01723 -0.0715 0.6169 1.0000
6.000 0.9533 0.02480 0.01761 -0.0701 0.6049 1.0000
6.250 0.9775 0.02475 0.01766 -0.0689 0.5934 1.0000
6.500 1.0059 0.02435 0.01735 -0.0680 0.5820 1.0000
6.750 1.0367 0.02371 0.01678 -0.0673 0.5702 1.0000
7.000 1.0651 0.02316 0.01633 -0.0664 0.5566 1.0000
7.250 1.0888 0.02281 0.01609 -0.0649 0.5408 1.0000
7.500 1.1110 0.02244 0.01587 -0.0631 0.5229 1.0000
7.750 1.1348 0.02188 0.01540 -0.0615 0.5029 1.0000
8.000 1.1547 0.02150 0.01515 -0.0594 0.4794 1.0000
8.250 1.1720 0.02125 0.01499 -0.0569 0.4507 1.0000
8.500 1.1853 0.02121 0.01495 -0.0539 0.4134 1.0000
8.750 1.1906 0.02165 0.01526 -0.0500 0.3613 1.0000
9.000 1.1870 0.02276 0.01594 -0.0453 0.2990 1.0000
9.250 1.1773 0.02433 0.01710 -0.0402 0.2461 1.0000
9.500 1.1661 0.02615 0.01859 -0.0354 0.2045 1.0000
9.750 1.1565 0.02820 0.02037 -0.0315 0.1716 1.0000
10.000 1.1474 0.03052 0.02248 -0.0283 0.1416 1.0000
10.250 1.1378 0.03315 0.02487 -0.0255 0.1164 1.0000
10.500 1.1294 0.03599 0.02756 -0.0232 0.0927 1.0000
10.750 1.1221 0.03900 0.03039 -0.0208 0.0752 1.0000
11.000 1.1219 0.04161 0.03291 -0.0189 0.0633 1.0000
11.250 1.1275 0.04375 0.03500 -0.0175 0.0561 1.0000
11.500 1.1407 0.04572 0.03703 -0.0159 0.0501 1.0000
11.750 1.1587 0.04747 0.03878 -0.0147 0.0466 1.0000
12.000 1.1968 0.04984 0.04112 -0.0138 0.0433 1.0000
12.250 1.2165 0.05246 0.04409 -0.0128 0.0421 1.0000
12.500 1.2268 0.05545 0.04740 -0.0117 0.0409 1.0000
12.750 1.2307 0.05853 0.05078 -0.0106 0.0401 1.0000
13.000 1.2298 0.06183 0.05437 -0.0095 0.0393 1.0000
13.250 1.2256 0.06528 0.05809 -0.0088 0.0387 1.0000
13.500 1.2173 0.06920 0.06228 -0.0082 0.0384 1.0000
13.750 1.2092 0.07298 0.06628 -0.0081 0.0377 1.0000
14.000 1.1901 0.07812 0.07176 -0.0085 0.0382 1.0000
14.250 1.1700 0.08356 0.07749 -0.0095 0.0385 1.0000
14.500 1.1473 0.08958 0.08378 -0.0114 0.0388 1.0000
14.750 1.1227 0.09623 0.09069 -0.0140 0.0392 1.0000
15.000 1.0950 0.10395 0.09864 -0.0177 0.0399 1.0000
15.250 1.0678 0.11243 0.10733 -0.0223 0.0410 1.0000
15.500 1.0402 0.12179 0.11685 -0.0280 0.0417 1.0000
15.750 1.0180 0.13110 0.12625 -0.0334 0.0427 1.0000
16.000 1.0009 0.14007 0.13527 -0.0385 0.0435 1.0000
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