E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E174 (Dicke 8.92%) (e174-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.54 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e174-il-1000000-n5.txt Download as CSV file: xf-e174-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E174 (Dicke 8.92%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3059 0.08224 0.08011 -0.0442 0.8304 0.0048
-8.250 -0.3045 0.07920 0.07697 -0.0451 0.8042 0.0047
-7.750 -0.3061 0.07252 0.07018 -0.0475 0.7658 0.0045
-7.500 -0.3102 0.06901 0.06665 -0.0492 0.7510 0.0045
-7.250 -0.3077 0.06452 0.06212 -0.0535 0.7380 0.0044
-7.000 -0.3020 0.05904 0.05658 -0.0594 0.7267 0.0043
-6.750 -0.2926 0.05242 0.04987 -0.0663 0.7176 0.0042
-6.250 -0.2847 0.01896 0.01472 -0.0810 0.7055 0.0046
-6.000 -0.2606 0.01670 0.01204 -0.0810 0.6970 0.0047
-5.750 -0.2349 0.01530 0.01033 -0.0810 0.6896 0.0049
-5.500 -0.2086 0.01430 0.00910 -0.0809 0.6820 0.0050
-5.250 -0.1819 0.01343 0.00803 -0.0809 0.6750 0.0051
-5.000 -0.1549 0.01271 0.00713 -0.0808 0.6678 0.0051
-4.750 -0.1276 0.01215 0.00643 -0.0808 0.6616 0.0052
-4.500 -0.1011 0.01109 0.00517 -0.0807 0.6550 0.0055
-4.250 -0.0738 0.01054 0.00453 -0.0806 0.6491 0.0058
-4.000 -0.0463 0.01009 0.00399 -0.0806 0.6430 0.0059
-3.500 0.0092 0.00933 0.00306 -0.0805 0.6319 0.0063
-3.250 0.0371 0.00903 0.00269 -0.0805 0.6260 0.0066
-3.000 0.0650 0.00877 0.00237 -0.0805 0.6211 0.0071
-2.750 0.0932 0.00856 0.00210 -0.0805 0.6159 0.0076
-2.500 0.1213 0.00840 0.00188 -0.0805 0.6104 0.0079
-2.250 0.1494 0.00821 0.00164 -0.0805 0.6056 0.0085
-2.000 0.1776 0.00805 0.00143 -0.0806 0.6006 0.0096
-1.750 0.2058 0.00794 0.00129 -0.0806 0.5954 0.0111
-1.500 0.2340 0.00782 0.00115 -0.0806 0.5907 0.0156
-1.250 0.2621 0.00760 0.00105 -0.0807 0.5858 0.0487
-1.000 0.2901 0.00745 0.00098 -0.0808 0.5809 0.0846
-0.750 0.3182 0.00729 0.00093 -0.0809 0.5762 0.1254
-0.500 0.3462 0.00710 0.00090 -0.0810 0.5711 0.1882
-0.250 0.3739 0.00686 0.00089 -0.0811 0.5661 0.2773
0.000 0.4019 0.00670 0.00088 -0.0813 0.5615 0.3414
0.250 0.4296 0.00646 0.00090 -0.0814 0.5563 0.4416
0.500 0.4573 0.00631 0.00092 -0.0814 0.5512 0.5176
0.750 0.4849 0.00613 0.00095 -0.0815 0.5462 0.6016
1.000 0.5117 0.00588 0.00100 -0.0813 0.5406 0.7152
1.250 0.5361 0.00561 0.00107 -0.0805 0.5352 0.8393
1.500 0.5624 0.00538 0.00109 -0.0798 0.5289 0.9645
1.750 0.5954 0.00545 0.00111 -0.0810 0.5211 1.0000
2.000 0.6234 0.00552 0.00115 -0.0810 0.5125 1.0000
2.250 0.6512 0.00561 0.00119 -0.0810 0.5036 1.0000
2.500 0.6788 0.00572 0.00125 -0.0810 0.4937 1.0000
2.750 0.7066 0.00581 0.00132 -0.0810 0.4840 1.0000
3.000 0.7342 0.00592 0.00139 -0.0810 0.4741 1.0000
3.250 0.7617 0.00604 0.00147 -0.0809 0.4629 1.0000
3.500 0.7891 0.00618 0.00157 -0.0809 0.4500 1.0000
3.750 0.8162 0.00635 0.00168 -0.0808 0.4316 1.0000
4.000 0.8421 0.00667 0.00183 -0.0806 0.3954 1.0000
4.250 0.8677 0.00701 0.00202 -0.0804 0.3584 1.0000
4.500 0.8919 0.00755 0.00231 -0.0800 0.3048 1.0000
4.750 0.9129 0.00850 0.00281 -0.0792 0.2146 1.0000
5.000 0.9358 0.00918 0.00320 -0.0787 0.1594 1.0000
5.250 0.9599 0.00969 0.00354 -0.0783 0.1237 1.0000
5.500 0.9832 0.01028 0.00395 -0.0778 0.0859 1.0000
5.750 1.0063 0.01088 0.00437 -0.0772 0.0529 1.0000
6.000 1.0287 0.01156 0.00487 -0.0766 0.0216 1.0000
6.250 1.0522 0.01206 0.00531 -0.0760 0.0097 1.0000
6.500 1.0770 0.01240 0.00567 -0.0756 0.0084 1.0000
6.750 1.1016 0.01276 0.00605 -0.0752 0.0076 1.0000
7.000 1.1258 0.01313 0.00646 -0.0748 0.0071 1.0000
7.250 1.1500 0.01350 0.00686 -0.0743 0.0069 1.0000
7.500 1.1737 0.01390 0.00730 -0.0738 0.0067 1.0000
7.750 1.1970 0.01432 0.00777 -0.0732 0.0063 1.0000
8.000 1.2197 0.01477 0.00827 -0.0726 0.0060 1.0000
8.250 1.2418 0.01528 0.00882 -0.0719 0.0058 1.0000
8.500 1.2633 0.01581 0.00940 -0.0711 0.0056 1.0000
8.750 1.2840 0.01638 0.01002 -0.0702 0.0054 1.0000
9.000 1.3037 0.01701 0.01071 -0.0691 0.0052 1.0000
9.250 1.3221 0.01772 0.01148 -0.0679 0.0050 1.0000
9.500 1.3387 0.01852 0.01236 -0.0665 0.0049 1.0000
9.750 1.3523 0.01950 0.01342 -0.0646 0.0047 1.0000
10.000 1.3614 0.02066 0.01468 -0.0622 0.0046 1.0000
10.250 1.3717 0.02146 0.01555 -0.0597 0.0045 1.0000
10.500 1.3827 0.02220 0.01637 -0.0575 0.0045 1.0000
10.750 1.3901 0.02321 0.01745 -0.0551 0.0045 1.0000
11.000 1.3988 0.02421 0.01853 -0.0530 0.0044 1.0000
11.250 1.4063 0.02537 0.01978 -0.0511 0.0043 1.0000
11.500 1.4131 0.02668 0.02118 -0.0493 0.0042 1.0000
11.750 1.4185 0.02820 0.02279 -0.0476 0.0042 1.0000
12.000 1.4237 0.02984 0.02453 -0.0462 0.0041 1.0000
12.250 1.4276 0.03169 0.02647 -0.0449 0.0041 1.0000
12.500 1.4363 0.03317 0.02803 -0.0441 0.0039 1.0000
12.750 1.4394 0.03528 0.03026 -0.0431 0.0039 1.0000
13.000 1.4434 0.03737 0.03245 -0.0424 0.0038 1.0000
13.250 1.4458 0.03971 0.03489 -0.0418 0.0037 1.0000
13.500 1.4473 0.04222 0.03751 -0.0413 0.0036 1.0000
13.750 1.4478 0.04493 0.04033 -0.0410 0.0036 1.0000
14.000 1.4494 0.04759 0.04309 -0.0408 0.0035 1.0000
14.250 1.4473 0.05075 0.04638 -0.0408 0.0035 1.0000
14.500 1.4445 0.05414 0.04989 -0.0410 0.0035 1.0000
14.750 1.4432 0.05742 0.05328 -0.0414 0.0034 1.0000
15.000 1.4394 0.06117 0.05715 -0.0421 0.0034 1.0000
15.250 1.4341 0.06532 0.06143 -0.0430 0.0033 1.0000
15.500 1.4303 0.06939 0.06561 -0.0441 0.0033 1.0000
15.750 1.4238 0.07401 0.07037 -0.0456 0.0033 1.0000
16.000 1.4172 0.07885 0.07533 -0.0472 0.0033 1.0000
16.250 1.4104 0.08394 0.08056 -0.0492 0.0032 1.0000
16.500 1.4024 0.08935 0.08610 -0.0515 0.0032 1.0000
16.750 1.3925 0.09533 0.09222 -0.0542 0.0032 1.0000
17.000 1.3839 0.10127 0.09828 -0.0570 0.0032 1.0000
17.250 1.3702 0.10838 0.10554 -0.0605 0.0032 1.0000
17.500 1.3595 0.11511 0.11239 -0.0640 0.0032 1.0000
17.750 1.3469 0.12247 0.11988 -0.0680 0.0032 1.0000
18.000 1.3337 0.13017 0.12772 -0.0724 0.0031 1.0000
18.250 1.3198 0.13826 0.13594 -0.0771 0.0031 1.0000
18.500 1.3054 0.14670 0.14451 -0.0821 0.0031 1.0000
18.750 1.2906 0.15553 0.15347 -0.0876 0.0031 1.0000
19.000 1.2755 0.16474 0.16282 -0.0933 0.0032 1.0000
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Polar data table (+)
Polar graphs
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