E176 (8.83%) (e176-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.63 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e176-il-1000000-n5.txt Download as CSV file: xf-e176-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E176 (8.83%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3929 0.08174 0.07978 -0.0315 0.8496 0.0060
-8.500 -0.3955 0.07810 0.07602 -0.0327 0.8185 0.0059
-8.250 -0.4021 0.07379 0.07165 -0.0344 0.7950 0.0060
-8.000 -0.4149 0.06911 0.06693 -0.0365 0.7754 0.0064
-7.750 -0.4168 0.06382 0.06159 -0.0417 0.7602 0.0063
-7.500 -0.4160 0.05682 0.05450 -0.0486 0.7476 0.0063
-7.250 -0.4152 0.04626 0.04375 -0.0564 0.7378 0.0066
-7.000 -0.4254 0.02754 0.02422 -0.0620 0.7311 0.0067
-6.750 -0.4090 0.02301 0.01917 -0.0623 0.7221 0.0067
-6.500 -0.3875 0.02048 0.01624 -0.0623 0.7137 0.0068
-6.250 -0.3638 0.01877 0.01423 -0.0622 0.7052 0.0069
-6.000 -0.3382 0.01783 0.01309 -0.0621 0.6976 0.0070
-5.750 -0.3126 0.01685 0.01190 -0.0620 0.6897 0.0071
-5.500 -0.2872 0.01552 0.01032 -0.0618 0.6827 0.0071
-5.250 -0.2614 0.01438 0.00896 -0.0617 0.6758 0.0072
-5.000 -0.2349 0.01351 0.00790 -0.0615 0.6694 0.0072
-4.750 -0.2097 0.01183 0.00596 -0.0612 0.6630 0.0074
-4.500 -0.1834 0.01090 0.00488 -0.0610 0.6574 0.0078
-4.250 -0.1563 0.01041 0.00431 -0.0609 0.6514 0.0081
-4.000 -0.1289 0.01005 0.00387 -0.0608 0.6456 0.0084
-3.750 -0.1013 0.00973 0.00350 -0.0608 0.6402 0.0088
-3.500 -0.0737 0.00943 0.00313 -0.0607 0.6346 0.0092
-3.250 -0.0459 0.00917 0.00280 -0.0607 0.6295 0.0096
-3.000 -0.0181 0.00890 0.00249 -0.0606 0.6243 0.0099
-2.750 0.0098 0.00868 0.00220 -0.0606 0.6193 0.0102
-2.500 0.0378 0.00849 0.00196 -0.0606 0.6145 0.0105
-2.250 0.0658 0.00834 0.00177 -0.0606 0.6093 0.0110
-2.000 0.0939 0.00820 0.00159 -0.0606 0.6045 0.0113
-1.750 0.1220 0.00806 0.00141 -0.0606 0.5999 0.0114
-1.500 0.1502 0.00793 0.00121 -0.0605 0.5947 0.0122
-1.000 0.2065 0.00771 0.00098 -0.0606 0.5855 0.0230
-0.750 0.2344 0.00751 0.00090 -0.0606 0.5804 0.0642
-0.250 0.2901 0.00710 0.00081 -0.0608 0.5708 0.1823
0.000 0.3175 0.00679 0.00080 -0.0609 0.5656 0.2869
0.250 0.3444 0.00639 0.00081 -0.0610 0.5607 0.4404
0.500 0.3714 0.00606 0.00084 -0.0609 0.5556 0.5661
0.750 0.3985 0.00587 0.00086 -0.0608 0.5500 0.6512
1.000 0.4244 0.00560 0.00090 -0.0604 0.5446 0.7606
1.250 0.4471 0.00529 0.00095 -0.0591 0.5376 0.8841
1.500 0.4837 0.00520 0.00097 -0.0608 0.5294 0.9837
1.750 0.5167 0.00527 0.00099 -0.0620 0.5205 1.0000
2.000 0.5442 0.00534 0.00103 -0.0619 0.5113 1.0000
2.250 0.5717 0.00543 0.00107 -0.0618 0.5015 1.0000
2.500 0.5991 0.00553 0.00112 -0.0617 0.4916 1.0000
2.750 0.6267 0.00562 0.00118 -0.0617 0.4814 1.0000
3.000 0.6542 0.00572 0.00126 -0.0616 0.4706 1.0000
3.250 0.6815 0.00584 0.00134 -0.0616 0.4581 1.0000
3.500 0.7087 0.00598 0.00143 -0.0615 0.4424 1.0000
3.750 0.7357 0.00615 0.00154 -0.0614 0.4241 1.0000
4.000 0.7624 0.00638 0.00168 -0.0612 0.3983 1.0000
4.250 0.7861 0.00702 0.00196 -0.0608 0.3222 1.0000
4.500 0.8069 0.00808 0.00247 -0.0601 0.2100 1.0000
4.750 0.8305 0.00873 0.00284 -0.0597 0.1521 1.0000
5.000 0.8544 0.00932 0.00321 -0.0593 0.1064 1.0000
5.250 0.8787 0.00983 0.00355 -0.0590 0.0727 1.0000
5.500 0.9025 0.01041 0.00395 -0.0585 0.0392 1.0000
5.750 0.9251 0.01111 0.00448 -0.0579 0.0081 1.0000
6.000 0.9505 0.01144 0.00481 -0.0576 0.0062 1.0000
6.250 0.9759 0.01176 0.00518 -0.0573 0.0054 1.0000
6.500 1.0009 0.01211 0.00556 -0.0569 0.0050 1.0000
6.750 1.0259 0.01244 0.00593 -0.0566 0.0048 1.0000
7.000 1.0504 0.01282 0.00635 -0.0562 0.0046 1.0000
7.250 1.0745 0.01323 0.00680 -0.0557 0.0043 1.0000
7.500 1.0980 0.01368 0.00732 -0.0552 0.0041 1.0000
7.750 1.1210 0.01419 0.00787 -0.0546 0.0039 1.0000
8.000 1.1434 0.01473 0.00847 -0.0539 0.0037 1.0000
8.250 1.1653 0.01530 0.00909 -0.0532 0.0035 1.0000
8.500 1.1865 0.01590 0.00973 -0.0524 0.0033 1.0000
8.750 1.2063 0.01661 0.01050 -0.0514 0.0031 1.0000
9.000 1.2232 0.01757 0.01155 -0.0500 0.0029 1.0000
9.250 1.2390 0.01855 0.01264 -0.0485 0.0029 1.0000
9.500 1.2513 0.01978 0.01398 -0.0466 0.0028 1.0000
9.750 1.2667 0.02063 0.01491 -0.0451 0.0027 1.0000
10.000 1.2815 0.02146 0.01581 -0.0435 0.0027 1.0000
10.250 1.2916 0.02236 0.01680 -0.0412 0.0027 1.0000
10.500 1.3000 0.02328 0.01780 -0.0387 0.0026 1.0000
10.750 1.3072 0.02435 0.01894 -0.0364 0.0026 1.0000
11.000 1.3129 0.02564 0.02033 -0.0342 0.0026 1.0000
11.250 1.3206 0.02686 0.02164 -0.0325 0.0025 1.0000
11.500 1.3259 0.02839 0.02327 -0.0309 0.0025 1.0000
11.750 1.3309 0.03005 0.02506 -0.0294 0.0025 1.0000
12.000 1.3368 0.03170 0.02681 -0.0283 0.0024 1.0000
12.250 1.3401 0.03371 0.02893 -0.0272 0.0024 1.0000
12.500 1.3445 0.03567 0.03100 -0.0263 0.0023 1.0000
12.750 1.3451 0.03815 0.03361 -0.0256 0.0023 1.0000
13.000 1.3476 0.04047 0.03605 -0.0251 0.0022 1.0000
13.250 1.3496 0.04292 0.03861 -0.0248 0.0022 1.0000
13.500 1.3463 0.04612 0.04195 -0.0246 0.0022 1.0000
13.750 1.3452 0.04912 0.04508 -0.0247 0.0021 1.0000
14.000 1.3397 0.05282 0.04893 -0.0251 0.0021 1.0000
14.250 1.3354 0.05646 0.05270 -0.0257 0.0021 1.0000
14.500 1.3308 0.06029 0.05666 -0.0266 0.0020 1.0000
14.750 1.3236 0.06470 0.06120 -0.0279 0.0020 1.0000
15.000 1.3146 0.06963 0.06628 -0.0295 0.0020 1.0000
15.250 1.3053 0.07487 0.07167 -0.0316 0.0019 1.0000
15.500 1.2920 0.08105 0.07800 -0.0342 0.0020 1.0000
15.750 1.2808 0.08722 0.08432 -0.0372 0.0019 1.0000
16.000 1.2668 0.09424 0.09149 -0.0407 0.0019 1.0000
16.250 1.2513 0.10188 0.09928 -0.0448 0.0019 1.0000
16.500 1.2322 0.11076 0.10833 -0.0497 0.0020 1.0000
16.750 1.2136 0.11997 0.11769 -0.0550 0.0020 1.0000
17.000 1.1996 0.12848 0.12631 -0.0600 0.0019 1.0000
17.250 1.1822 0.13823 0.13620 -0.0658 0.0019 1.0000
17.500 1.1603 0.14960 0.14772 -0.0725 0.0020 1.0000
17.750 1.1382 0.16165 0.15990 -0.0796 0.0020 1.0000
18.000 1.1138 0.17522 0.17360 -0.0874 0.0021 1.0000
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Polar data table (+)
Polar graphs
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