E195 (11.82%) (e195-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E195 (11.82%) (e195-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.2 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e195-il-1000000-n5.txt Download as CSV file: xf-e195-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5766 0.08187 0.08014 -0.0433 1.0000 0.0071
-12.000 -0.7165 0.04725 0.04518 -0.0672 1.0000 0.0066
-11.750 -0.7441 0.03866 0.03637 -0.0761 1.0000 0.0066
-11.500 -0.7692 0.03515 0.03271 -0.0756 1.0000 0.0066
-11.250 -0.7728 0.03219 0.02954 -0.0755 0.9911 0.0067
-11.000 -0.7570 0.02897 0.02602 -0.0784 0.9825 0.0068
-10.750 -0.7346 0.02687 0.02370 -0.0804 0.9702 0.0069
-10.500 -0.7109 0.02488 0.02146 -0.0821 0.9481 0.0070
-10.250 -0.6922 0.02327 0.01955 -0.0821 0.9095 0.0070
-10.000 -0.6759 0.02238 0.01840 -0.0808 0.8745 0.0071
-9.750 -0.6604 0.02123 0.01699 -0.0795 0.8478 0.0072
-9.500 -0.6418 0.02040 0.01595 -0.0785 0.8254 0.0072
-9.250 -0.6219 0.01958 0.01493 -0.0776 0.8062 0.0073
-9.000 -0.6009 0.01884 0.01400 -0.0769 0.7895 0.0073
-8.750 -0.5815 0.01767 0.01262 -0.0760 0.7753 0.0074
-8.500 -0.5630 0.01630 0.01102 -0.0750 0.7619 0.0076
-8.250 -0.5412 0.01544 0.01001 -0.0743 0.7494 0.0077
-8.000 -0.5183 0.01473 0.00916 -0.0737 0.7378 0.0078
-7.750 -0.4942 0.01417 0.00850 -0.0732 0.7278 0.0080
-7.500 -0.4697 0.01368 0.00790 -0.0728 0.7180 0.0081
-7.250 -0.4446 0.01327 0.00741 -0.0725 0.7087 0.0083
-7.000 -0.4192 0.01286 0.00692 -0.0722 0.7004 0.0086
-6.500 -0.3682 0.01205 0.00594 -0.0716 0.6849 0.0090
-6.000 -0.3163 0.01131 0.00503 -0.0710 0.6713 0.0095
-5.750 -0.2901 0.01100 0.00464 -0.0708 0.6646 0.0098
-5.500 -0.2635 0.01071 0.00429 -0.0706 0.6588 0.0100
-5.250 -0.2368 0.01045 0.00396 -0.0704 0.6527 0.0103
-5.000 -0.2099 0.01022 0.00367 -0.0702 0.6473 0.0104
-4.750 -0.1827 0.01000 0.00341 -0.0701 0.6419 0.0106
-4.500 -0.1561 0.00970 0.00303 -0.0699 0.6363 0.0110
-4.250 -0.1290 0.00946 0.00274 -0.0698 0.6316 0.0115
-4.000 -0.1016 0.00926 0.00250 -0.0697 0.6267 0.0121
-3.750 -0.0743 0.00910 0.00230 -0.0696 0.6215 0.0128
-3.500 -0.0467 0.00896 0.00212 -0.0696 0.6171 0.0138
-3.250 -0.0189 0.00884 0.00196 -0.0695 0.6126 0.0147
-3.000 0.0087 0.00870 0.00181 -0.0695 0.6078 0.0175
-2.750 0.0356 0.00845 0.00164 -0.0694 0.6034 0.0412
-2.500 0.0632 0.00827 0.00152 -0.0693 0.5994 0.0605
-2.250 0.0906 0.00809 0.00142 -0.0693 0.5949 0.0867
-2.000 0.1178 0.00791 0.00133 -0.0693 0.5904 0.1191
-1.500 0.1722 0.00747 0.00118 -0.0693 0.5824 0.2138
-1.250 0.1996 0.00733 0.00113 -0.0692 0.5779 0.2523
-1.000 0.2265 0.00710 0.00109 -0.0692 0.5739 0.3166
-0.750 0.2533 0.00684 0.00107 -0.0691 0.5699 0.3939
-0.500 0.2808 0.00673 0.00106 -0.0691 0.5655 0.4370
-0.250 0.3085 0.00669 0.00106 -0.0691 0.5611 0.4633
0.000 0.3364 0.00662 0.00106 -0.0691 0.5573 0.4932
0.250 0.3642 0.00656 0.00107 -0.0691 0.5529 0.5221
0.500 0.3918 0.00651 0.00108 -0.0691 0.5483 0.5513
1.000 0.4469 0.00639 0.00114 -0.0691 0.5398 0.6164
1.250 0.4741 0.00633 0.00117 -0.0689 0.5349 0.6543
1.500 0.5010 0.00627 0.00122 -0.0688 0.5304 0.6951
1.750 0.5279 0.00619 0.00127 -0.0686 0.5253 0.7389
2.000 0.5538 0.00611 0.00133 -0.0681 0.5192 0.7903
2.250 0.5786 0.00600 0.00140 -0.0674 0.5131 0.8514
2.500 0.6028 0.00592 0.00149 -0.0664 0.5057 0.9194
2.750 0.6369 0.00597 0.00156 -0.0677 0.4972 0.9610
3.000 0.6717 0.00607 0.00164 -0.0693 0.4877 0.9772
3.250 0.7058 0.00616 0.00170 -0.0707 0.4783 0.9861
3.500 0.7400 0.00627 0.00178 -0.0722 0.4677 0.9923
3.750 0.7735 0.00639 0.00186 -0.0736 0.4557 0.9974
4.000 0.8036 0.00653 0.00197 -0.0742 0.4433 1.0000
4.250 0.8279 0.00669 0.00208 -0.0735 0.4295 1.0000
4.500 0.8520 0.00686 0.00220 -0.0729 0.4137 1.0000
4.750 0.8751 0.00712 0.00236 -0.0720 0.3889 1.0000
5.000 0.8966 0.00750 0.00258 -0.0710 0.3512 1.0000
5.250 0.9172 0.00799 0.00286 -0.0698 0.3082 1.0000
5.500 0.9340 0.00876 0.00330 -0.0681 0.2433 1.0000
5.750 0.9513 0.00951 0.00374 -0.0664 0.1861 1.0000
6.000 0.9712 0.01006 0.00412 -0.0652 0.1498 1.0000
6.250 0.9912 0.01060 0.00450 -0.0640 0.1184 1.0000
6.500 1.0117 0.01109 0.00487 -0.0629 0.0947 1.0000
6.750 1.0325 0.01155 0.00523 -0.0619 0.0746 1.0000
7.000 1.0525 0.01205 0.00564 -0.0607 0.0558 1.0000
7.250 1.0711 0.01262 0.00610 -0.0593 0.0365 1.0000
7.500 1.0888 0.01323 0.00661 -0.0578 0.0199 1.0000
7.750 1.1056 0.01388 0.00718 -0.0561 0.0081 1.0000
8.000 1.1254 0.01430 0.00761 -0.0549 0.0066 1.0000
8.250 1.1453 0.01469 0.00804 -0.0538 0.0060 1.0000
8.500 1.1646 0.01509 0.00847 -0.0525 0.0057 1.0000
8.750 1.1829 0.01551 0.00892 -0.0511 0.0054 1.0000
9.000 1.1982 0.01596 0.00941 -0.0491 0.0051 1.0000
9.250 1.2121 0.01644 0.00992 -0.0469 0.0050 1.0000
9.500 1.2254 0.01696 0.01048 -0.0447 0.0047 1.0000
9.750 1.2377 0.01756 0.01113 -0.0425 0.0045 1.0000
10.000 1.2488 0.01825 0.01188 -0.0402 0.0044 1.0000
10.250 1.2581 0.01908 0.01277 -0.0378 0.0042 1.0000
10.500 1.2678 0.01993 0.01369 -0.0357 0.0040 1.0000
10.750 1.2784 0.02078 0.01459 -0.0338 0.0039 1.0000
11.000 1.2895 0.02164 0.01551 -0.0322 0.0039 1.0000
11.250 1.2990 0.02266 0.01659 -0.0305 0.0038 1.0000
11.500 1.3087 0.02372 0.01772 -0.0290 0.0037 1.0000
11.750 1.3187 0.02481 0.01887 -0.0276 0.0036 1.0000
12.000 1.3265 0.02613 0.02025 -0.0263 0.0035 1.0000
12.250 1.3345 0.02749 0.02168 -0.0250 0.0034 1.0000
12.500 1.3396 0.02915 0.02342 -0.0238 0.0033 1.0000
12.750 1.3470 0.03068 0.02502 -0.0228 0.0033 1.0000
13.000 1.3536 0.03232 0.02673 -0.0219 0.0032 1.0000
13.250 1.3579 0.03422 0.02871 -0.0210 0.0032 1.0000
13.500 1.3615 0.03625 0.03082 -0.0202 0.0031 1.0000
13.750 1.3645 0.03839 0.03304 -0.0196 0.0031 1.0000
14.000 1.3684 0.04050 0.03524 -0.0191 0.0030 1.0000
14.250 1.3707 0.04280 0.03762 -0.0186 0.0030 1.0000
14.500 1.3730 0.04519 0.04009 -0.0183 0.0030 1.0000
14.750 1.3741 0.04778 0.04276 -0.0181 0.0029 1.0000
15.000 1.3746 0.05052 0.04559 -0.0181 0.0029 1.0000
15.250 1.3753 0.05332 0.04847 -0.0182 0.0028 1.0000
15.500 1.3739 0.05647 0.05171 -0.0184 0.0028 1.0000
15.750 1.3730 0.05965 0.05498 -0.0188 0.0028 1.0000
16.000 1.3706 0.06312 0.05855 -0.0194 0.0027 1.0000
16.250 1.3687 0.06664 0.06216 -0.0201 0.0027 1.0000
16.500 1.3634 0.07074 0.06636 -0.0211 0.0027 1.0000
16.750 1.3584 0.07494 0.07067 -0.0223 0.0027 1.0000
17.000 1.3511 0.07957 0.07541 -0.0238 0.0026 1.0000
17.250 1.3462 0.08401 0.07995 -0.0253 0.0026 1.0000
17.500 1.3352 0.08955 0.08563 -0.0273 0.0026 1.0000
17.750 1.3283 0.09454 0.09073 -0.0293 0.0026 1.0000
18.000 1.3174 0.10036 0.09667 -0.0318 0.0025 1.0000
18.250 1.3076 0.10617 0.10259 -0.0344 0.0025 1.0000
18.500 1.2989 0.11189 0.10843 -0.0371 0.0025 1.0000
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Polar data table (+)
Polar graphs
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