E195 (11.82%) (e195-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E195 (11.82%) (e195-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.13 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e195-il-1000000.txt Download as CSV file: xf-e195-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4233 0.08176 0.08020 -0.0445 1.0000 0.0146
-9.750 -0.4263 0.07767 0.07613 -0.0464 1.0000 0.0148
-9.500 -0.4345 0.07260 0.07110 -0.0489 1.0000 0.0150
-9.250 -0.5362 0.04236 0.04047 -0.0750 0.9883 0.0146
-9.000 -0.5201 0.03817 0.03607 -0.0799 0.9785 0.0148
-8.750 -0.5284 0.02738 0.02440 -0.0832 0.9532 0.0122
-8.500 -0.5176 0.02349 0.01999 -0.0825 0.9209 0.0120
-8.250 -0.5071 0.02053 0.01651 -0.0805 0.8879 0.0119
-8.000 -0.4895 0.01901 0.01467 -0.0791 0.8627 0.0120
-7.750 -0.4697 0.01780 0.01319 -0.0780 0.8409 0.0122
-7.500 -0.4486 0.01668 0.01183 -0.0770 0.8221 0.0123
-7.250 -0.4261 0.01576 0.01069 -0.0762 0.8051 0.0125
-7.000 -0.4032 0.01484 0.00959 -0.0754 0.7899 0.0126
-6.750 -0.3792 0.01415 0.00875 -0.0748 0.7763 0.0128
-6.500 -0.3552 0.01344 0.00790 -0.0742 0.7636 0.0130
-6.250 -0.3307 0.01282 0.00715 -0.0737 0.7518 0.0131
-6.000 -0.3056 0.01229 0.00651 -0.0732 0.7412 0.0133
-5.750 -0.2793 0.01203 0.00616 -0.0729 0.7315 0.0136
-5.500 -0.2558 0.01119 0.00519 -0.0722 0.7221 0.0140
-5.250 -0.2313 0.01053 0.00442 -0.0717 0.7136 0.0145
-4.750 -0.1790 0.00980 0.00354 -0.0711 0.6981 0.0158
-4.250 -0.1252 0.00930 0.00292 -0.0707 0.6842 0.0172
-4.000 -0.0981 0.00912 0.00266 -0.0705 0.6777 0.0178
-3.750 -0.0709 0.00888 0.00236 -0.0704 0.6717 0.0194
-3.500 -0.0436 0.00867 0.00213 -0.0702 0.6656 0.0232
-3.250 -0.0176 0.00828 0.00189 -0.0700 0.6602 0.0623
-3.000 0.0093 0.00797 0.00174 -0.0699 0.6548 0.1043
-2.750 0.0362 0.00773 0.00161 -0.0698 0.6493 0.1452
-2.500 0.0630 0.00750 0.00151 -0.0697 0.6443 0.1912
-2.250 0.0901 0.00725 0.00142 -0.0697 0.6394 0.2439
-2.000 0.1167 0.00700 0.00135 -0.0696 0.6344 0.3079
-1.750 0.1434 0.00677 0.00130 -0.0695 0.6297 0.3745
-1.500 0.1707 0.00659 0.00127 -0.0695 0.6250 0.4290
-1.250 0.1980 0.00646 0.00125 -0.0694 0.6203 0.4750
-0.750 0.2526 0.00623 0.00123 -0.0692 0.6113 0.5633
-0.500 0.2801 0.00616 0.00123 -0.0691 0.6067 0.5965
-0.250 0.3072 0.00610 0.00124 -0.0690 0.6022 0.6334
0.000 0.3345 0.00599 0.00125 -0.0689 0.5980 0.6749
0.250 0.3613 0.00588 0.00127 -0.0686 0.5935 0.7223
0.500 0.3873 0.00578 0.00130 -0.0682 0.5890 0.7738
0.750 0.4126 0.00566 0.00135 -0.0675 0.5847 0.8307
1.000 0.4371 0.00553 0.00140 -0.0665 0.5804 0.8943
1.250 0.4670 0.00552 0.00147 -0.0667 0.5757 0.9486
1.500 0.5035 0.00559 0.00152 -0.0685 0.5709 0.9730
1.750 0.5419 0.00562 0.00155 -0.0708 0.5658 0.9851
2.000 0.5830 0.00569 0.00157 -0.0738 0.5600 0.9915
2.250 0.6239 0.00574 0.00160 -0.0767 0.5539 0.9970
2.500 0.6607 0.00578 0.00162 -0.0787 0.5471 1.0000
2.750 0.6853 0.00585 0.00167 -0.0781 0.5409 1.0000
3.000 0.7104 0.00590 0.00172 -0.0775 0.5343 1.0000
3.250 0.7349 0.00600 0.00178 -0.0769 0.5277 1.0000
3.500 0.7603 0.00605 0.00183 -0.0764 0.5204 1.0000
3.750 0.7850 0.00615 0.00190 -0.0758 0.5131 1.0000
4.000 0.8105 0.00622 0.00198 -0.0753 0.5051 1.0000
4.250 0.8355 0.00632 0.00207 -0.0748 0.4970 1.0000
4.500 0.8605 0.00642 0.00216 -0.0742 0.4870 1.0000
4.750 0.8858 0.00652 0.00227 -0.0737 0.4778 1.0000
5.000 0.9107 0.00666 0.00238 -0.0732 0.4675 1.0000
5.250 0.9352 0.00682 0.00250 -0.0726 0.4497 1.0000
5.500 0.9586 0.00707 0.00265 -0.0718 0.4253 1.0000
5.750 0.9816 0.00736 0.00284 -0.0710 0.3973 1.0000
6.000 1.0027 0.00781 0.00310 -0.0699 0.3548 1.0000
6.250 1.0228 0.00835 0.00343 -0.0687 0.3086 1.0000
6.500 1.0414 0.00901 0.00384 -0.0673 0.2588 1.0000
6.750 1.0596 0.00968 0.00430 -0.0659 0.2137 1.0000
7.000 1.0773 0.01038 0.00477 -0.0643 0.1706 1.0000
7.250 1.0955 0.01104 0.00523 -0.0629 0.1342 1.0000
7.500 1.1123 0.01175 0.00575 -0.0613 0.0989 1.0000
7.750 1.1290 0.01245 0.00628 -0.0596 0.0704 1.0000
8.000 1.1445 0.01318 0.00686 -0.0578 0.0454 1.0000
8.250 1.1556 0.01415 0.00763 -0.0553 0.0178 1.0000
8.500 1.1711 0.01480 0.00824 -0.0534 0.0111 1.0000
8.750 1.1876 0.01534 0.00881 -0.0516 0.0096 1.0000
9.000 1.2017 0.01588 0.00939 -0.0494 0.0088 1.0000
9.250 1.2129 0.01649 0.01006 -0.0467 0.0083 1.0000
9.500 1.2259 0.01703 0.01066 -0.0445 0.0080 1.0000
9.750 1.2380 0.01765 0.01132 -0.0422 0.0079 1.0000
10.000 1.2488 0.01836 0.01210 -0.0399 0.0074 1.0000
10.250 1.2587 0.01916 0.01296 -0.0376 0.0071 1.0000
10.500 1.2683 0.02003 0.01388 -0.0354 0.0070 1.0000
10.750 1.2761 0.02105 0.01497 -0.0332 0.0067 1.0000
11.000 1.2805 0.02236 0.01635 -0.0309 0.0064 1.0000
11.250 1.2862 0.02369 0.01776 -0.0290 0.0063 1.0000
11.500 1.2825 0.02580 0.01998 -0.0265 0.0061 1.0000
11.750 1.2851 0.02758 0.02185 -0.0249 0.0059 1.0000
12.000 1.2893 0.02932 0.02367 -0.0235 0.0059 1.0000
12.250 1.2953 0.03098 0.02541 -0.0224 0.0059 1.0000
12.500 1.2994 0.03287 0.02738 -0.0214 0.0058 1.0000
12.750 1.3037 0.03480 0.02939 -0.0205 0.0057 1.0000
13.000 1.3070 0.03688 0.03155 -0.0196 0.0057 1.0000
13.250 1.3091 0.03912 0.03388 -0.0189 0.0057 1.0000
13.500 1.3146 0.04109 0.03593 -0.0184 0.0056 1.0000
13.750 1.3109 0.04403 0.03898 -0.0176 0.0056 1.0000
14.000 1.3165 0.04608 0.04110 -0.0174 0.0055 1.0000
14.250 1.3184 0.04860 0.04371 -0.0172 0.0054 1.0000
14.500 1.3157 0.05168 0.04689 -0.0168 0.0055 1.0000
14.750 1.3163 0.05451 0.04982 -0.0168 0.0054 1.0000
15.000 1.3186 0.05723 0.05262 -0.0170 0.0052 1.0000
15.250 1.3173 0.06042 0.05591 -0.0172 0.0053 1.0000
15.500 1.3161 0.06372 0.05931 -0.0175 0.0052 1.0000
15.750 1.3160 0.06699 0.06268 -0.0182 0.0051 1.0000
16.000 1.3128 0.07073 0.06654 -0.0188 0.0051 1.0000
16.250 1.3123 0.07426 0.07015 -0.0198 0.0050 1.0000
16.500 1.3068 0.07853 0.07455 -0.0208 0.0051 1.0000
16.750 1.3029 0.08276 0.07891 -0.0221 0.0050 1.0000
17.000 1.3000 0.08696 0.08320 -0.0238 0.0048 1.0000
17.250 1.2942 0.09170 0.08805 -0.0255 0.0048 1.0000
17.500 1.2872 0.09674 0.09322 -0.0274 0.0048 1.0000
17.750 1.2788 0.10219 0.09881 -0.0297 0.0048 1.0000
18.000 1.2714 0.10760 0.10433 -0.0322 0.0048 1.0000
18.250 1.2619 0.11354 0.11041 -0.0351 0.0048 1.0000
18.500 1.2532 0.11955 0.11653 -0.0382 0.0047 1.0000
18.750 1.2436 0.12584 0.12294 -0.0416 0.0047 1.0000
19.000 1.2258 0.13396 0.13126 -0.0460 0.0048 1.0000
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Polar data table (+)
Polar graphs
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