E195 (11.82%) (e195-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E195 (11.82%) (e195-il) Reynolds number: 500,000 Max Cl/Cd: 112.4 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e195-il-500000.txt Download as CSV file: xf-e195-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3851 0.08535 0.08317 -0.0436 1.0000 0.0267
-9.250 -0.3880 0.08139 0.07925 -0.0452 1.0000 0.0275
-9.000 -0.3961 0.07644 0.07435 -0.0477 1.0000 0.0286
-8.000 -0.4423 0.04023 0.03720 -0.0812 0.9630 0.0316
-7.750 -0.4180 0.03709 0.03403 -0.0835 0.9486 0.0325
-7.500 -0.4290 0.02225 0.01745 -0.0813 0.9191 0.0190
-7.250 -0.4065 0.02051 0.01533 -0.0806 0.8976 0.0187
-7.000 -0.3845 0.01925 0.01378 -0.0796 0.8756 0.0185
-6.750 -0.3631 0.01773 0.01199 -0.0785 0.8564 0.0186
-6.500 -0.3412 0.01641 0.01047 -0.0776 0.8390 0.0190
-6.250 -0.3181 0.01551 0.00941 -0.0768 0.8231 0.0196
-6.000 -0.2944 0.01469 0.00843 -0.0761 0.8089 0.0199
-5.750 -0.2705 0.01392 0.00752 -0.0753 0.7958 0.0202
-5.500 -0.2462 0.01326 0.00674 -0.0747 0.7838 0.0207
-5.250 -0.2215 0.01269 0.00606 -0.0741 0.7729 0.0213
-5.000 -0.1966 0.01221 0.00545 -0.0735 0.7632 0.0222
-4.750 -0.1711 0.01177 0.00491 -0.0730 0.7536 0.0229
-4.500 -0.1452 0.01142 0.00446 -0.0726 0.7449 0.0236
-4.250 -0.1200 0.01091 0.00385 -0.0721 0.7367 0.0259
-4.000 -0.0934 0.01064 0.00353 -0.0719 0.7289 0.0292
-3.750 -0.0672 0.01029 0.00314 -0.0715 0.7217 0.0386
-3.500 -0.0421 0.00969 0.00281 -0.0711 0.7145 0.0999
-3.250 -0.0160 0.00939 0.00261 -0.0709 0.7079 0.1462
-3.000 0.0102 0.00908 0.00247 -0.0708 0.7016 0.1983
-2.750 0.0361 0.00873 0.00234 -0.0706 0.6952 0.2689
-2.500 0.0619 0.00843 0.00224 -0.0704 0.6896 0.3434
-2.250 0.0883 0.00818 0.00218 -0.0702 0.6835 0.4088
-2.000 0.1146 0.00800 0.00214 -0.0700 0.6780 0.4729
-1.750 0.1412 0.00787 0.00212 -0.0697 0.6726 0.5205
-1.500 0.1679 0.00773 0.00209 -0.0695 0.6670 0.5652
-1.250 0.1942 0.00762 0.00207 -0.0691 0.6621 0.6132
-1.000 0.2207 0.00751 0.00207 -0.0688 0.6569 0.6555
-0.750 0.2469 0.00739 0.00207 -0.0684 0.6516 0.7004
-0.500 0.2725 0.00729 0.00208 -0.0678 0.6470 0.7501
-0.250 0.2974 0.00716 0.00212 -0.0670 0.6421 0.8066
0.000 0.3220 0.00703 0.00216 -0.0659 0.6370 0.8682
0.250 0.3532 0.00703 0.00221 -0.0662 0.6325 0.9253
0.500 0.3934 0.00709 0.00226 -0.0687 0.6275 0.9595
0.750 0.4352 0.00713 0.00227 -0.0716 0.6222 0.9782
1.000 0.4793 0.00721 0.00226 -0.0752 0.6175 0.9890
1.250 0.5246 0.00724 0.00228 -0.0790 0.6123 0.9979
1.500 0.5553 0.00728 0.00229 -0.0798 0.6072 1.0000
1.750 0.5797 0.00737 0.00232 -0.0791 0.6027 1.0000
2.000 0.6041 0.00744 0.00238 -0.0785 0.5977 1.0000
2.250 0.6288 0.00750 0.00243 -0.0779 0.5923 1.0000
2.500 0.6537 0.00761 0.00248 -0.0773 0.5874 1.0000
2.750 0.6785 0.00766 0.00256 -0.0767 0.5814 1.0000
3.000 0.7034 0.00773 0.00262 -0.0761 0.5754 1.0000
3.250 0.7283 0.00782 0.00269 -0.0756 0.5692 1.0000
3.500 0.7532 0.00788 0.00276 -0.0750 0.5622 1.0000
3.750 0.7782 0.00799 0.00284 -0.0744 0.5559 1.0000
4.000 0.8033 0.00804 0.00294 -0.0739 0.5485 1.0000
4.250 0.8283 0.00815 0.00303 -0.0733 0.5413 1.0000
4.500 0.8535 0.00822 0.00313 -0.0728 0.5330 1.0000
4.750 0.8787 0.00832 0.00325 -0.0723 0.5251 1.0000
5.000 0.9037 0.00842 0.00335 -0.0717 0.5159 1.0000
5.250 0.9290 0.00851 0.00348 -0.0712 0.5061 1.0000
5.500 0.9540 0.00864 0.00361 -0.0707 0.4963 1.0000
5.750 0.9785 0.00878 0.00376 -0.0701 0.4841 1.0000
6.000 1.0026 0.00892 0.00390 -0.0694 0.4657 1.0000
6.250 1.0256 0.00914 0.00407 -0.0686 0.4429 1.0000
6.500 1.0481 0.00942 0.00429 -0.0677 0.4158 1.0000
6.750 1.0687 0.00983 0.00457 -0.0665 0.3801 1.0000
7.000 1.0861 0.01046 0.00498 -0.0649 0.3288 1.0000
7.250 1.1000 0.01137 0.00556 -0.0628 0.2683 1.0000
7.500 1.1140 0.01227 0.00619 -0.0608 0.2165 1.0000
7.750 1.1280 0.01314 0.00683 -0.0588 0.1729 1.0000
8.000 1.1412 0.01403 0.00750 -0.0567 0.1333 1.0000
8.250 1.1543 0.01487 0.00817 -0.0546 0.1026 1.0000
8.500 1.1664 0.01571 0.00886 -0.0523 0.0759 1.0000
8.750 1.1722 0.01678 0.00972 -0.0490 0.0449 1.0000
9.000 1.1723 0.01796 0.01074 -0.0448 0.0224 1.0000
9.250 1.1785 0.01892 0.01167 -0.0417 0.0165 1.0000
9.500 1.1872 0.01981 0.01263 -0.0391 0.0147 1.0000
9.750 1.1975 0.02065 0.01355 -0.0369 0.0139 1.0000
10.000 1.2057 0.02167 0.01463 -0.0347 0.0129 1.0000
10.250 1.2116 0.02289 0.01591 -0.0324 0.0121 1.0000
10.500 1.2164 0.02428 0.01738 -0.0303 0.0118 1.0000
10.750 1.2161 0.02613 0.01934 -0.0280 0.0113 1.0000
11.000 1.2221 0.02765 0.02095 -0.0265 0.0111 1.0000
11.250 1.2269 0.02932 0.02271 -0.0250 0.0110 1.0000
11.500 1.2304 0.03118 0.02468 -0.0237 0.0108 1.0000
11.750 1.2346 0.03307 0.02665 -0.0225 0.0105 1.0000
12.000 1.2372 0.03515 0.02883 -0.0214 0.0104 1.0000
12.250 1.2401 0.03727 0.03104 -0.0204 0.0102 1.0000
12.500 1.2423 0.03952 0.03338 -0.0195 0.0100 1.0000
12.750 1.2459 0.04168 0.03563 -0.0188 0.0098 1.0000
13.000 1.2493 0.04389 0.03792 -0.0182 0.0096 1.0000
13.250 1.2526 0.04616 0.04027 -0.0176 0.0095 1.0000
13.500 1.2565 0.04841 0.04257 -0.0173 0.0091 1.0000
13.750 1.2575 0.05104 0.04532 -0.0166 0.0091 1.0000
14.000 1.2606 0.05348 0.04783 -0.0164 0.0089 1.0000
14.250 1.2624 0.05615 0.05059 -0.0160 0.0088 1.0000
14.500 1.2654 0.05877 0.05331 -0.0157 0.0088 1.0000
14.750 1.2672 0.06161 0.05626 -0.0154 0.0087 1.0000
15.000 1.2680 0.06470 0.05947 -0.0150 0.0085 1.0000
15.250 1.2695 0.06772 0.06263 -0.0152 0.0086 1.0000
15.500 1.2678 0.07136 0.06643 -0.0153 0.0085 1.0000
15.750 1.2641 0.07536 0.07060 -0.0157 0.0085 1.0000
16.000 1.2614 0.07919 0.07457 -0.0167 0.0085 1.0000
16.250 1.2504 0.08456 0.08016 -0.0179 0.0084 1.0000
16.500 1.2467 0.08873 0.08446 -0.0195 0.0085 1.0000
16.750 1.2369 0.09412 0.09003 -0.0215 0.0085 1.0000
17.000 1.2220 0.10057 0.09668 -0.0242 0.0084 1.0000
17.250 1.2133 0.10610 0.10235 -0.0269 0.0085 1.0000
17.500 1.2043 0.11189 0.10830 -0.0299 0.0085 1.0000
17.750 1.1940 0.11816 0.11473 -0.0334 0.0086 1.0000
18.000 1.1821 0.12496 0.12169 -0.0373 0.0086 1.0000
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Polar data table (+)
Polar graphs
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