E176 (8.83%) (e176-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 500,000 Max Cl/Cd: 103.38 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e176-il-500000-n5.txt Download as CSV file: xf-e176-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4053 0.08838 0.08621 -0.0221 1.0000 0.0106
-8.500 -0.4032 0.08487 0.08273 -0.0236 1.0000 0.0102
-8.250 -0.4032 0.08092 0.07882 -0.0256 1.0000 0.0100
-8.000 -0.3890 0.07476 0.07263 -0.0336 0.9413 0.0101
-7.750 -0.3841 0.07011 0.06783 -0.0386 0.8812 0.0098
-7.500 -0.3847 0.06568 0.06327 -0.0424 0.8465 0.0096
-7.250 -0.3826 0.05993 0.05740 -0.0478 0.8224 0.0098
-7.000 -0.3763 0.05364 0.05095 -0.0532 0.8042 0.0097
-6.750 -0.3674 0.04641 0.04349 -0.0581 0.7895 0.0095
-6.500 -0.3561 0.03863 0.03536 -0.0615 0.7771 0.0096
-6.250 -0.3427 0.03125 0.02749 -0.0631 0.7666 0.0096
-6.000 -0.3243 0.02648 0.02222 -0.0635 0.7566 0.0101
-5.750 -0.3034 0.02293 0.01817 -0.0635 0.7467 0.0101
-5.500 -0.2806 0.02013 0.01490 -0.0633 0.7376 0.0100
-5.250 -0.2562 0.01809 0.01245 -0.0630 0.7291 0.0100
-5.000 -0.2306 0.01649 0.01050 -0.0627 0.7206 0.0101
-4.750 -0.2045 0.01525 0.00898 -0.0625 0.7128 0.0102
-4.500 -0.1781 0.01424 0.00775 -0.0622 0.7049 0.0104
-4.250 -0.1513 0.01343 0.00676 -0.0620 0.6978 0.0107
-4.000 -0.1244 0.01278 0.00596 -0.0618 0.6905 0.0110
-3.750 -0.0972 0.01228 0.00535 -0.0616 0.6839 0.0113
-3.500 -0.0701 0.01178 0.00473 -0.0614 0.6773 0.0115
-3.250 -0.0434 0.01103 0.00386 -0.0612 0.6713 0.0121
-3.000 -0.0162 0.01055 0.00330 -0.0611 0.6649 0.0129
-2.750 0.0112 0.01025 0.00293 -0.0610 0.6592 0.0140
-2.500 0.0390 0.00997 0.00257 -0.0610 0.6532 0.0145
-2.250 0.0667 0.00976 0.00227 -0.0609 0.6475 0.0149
-2.000 0.0946 0.00957 0.00202 -0.0608 0.6422 0.0157
-1.750 0.1226 0.00942 0.00180 -0.0608 0.6367 0.0170
-1.500 0.1505 0.00929 0.00162 -0.0607 0.6315 0.0221
-1.250 0.1782 0.00902 0.00149 -0.0607 0.6261 0.0599
-1.000 0.2056 0.00871 0.00140 -0.0608 0.6209 0.1281
-0.750 0.2328 0.00837 0.00134 -0.0608 0.6160 0.2231
-0.500 0.2601 0.00809 0.00130 -0.0609 0.6106 0.3088
-0.250 0.2861 0.00756 0.00131 -0.0609 0.6057 0.4869
0.000 0.3106 0.00701 0.00134 -0.0603 0.6010 0.6730
0.250 0.3337 0.00662 0.00137 -0.0591 0.5958 0.8072
0.500 0.3656 0.00636 0.00137 -0.0594 0.5907 0.9527
0.750 0.4061 0.00637 0.00134 -0.0622 0.5854 1.0000
1.000 0.4335 0.00643 0.00135 -0.0620 0.5798 1.0000
1.250 0.4607 0.00650 0.00136 -0.0619 0.5748 1.0000
1.500 0.4883 0.00656 0.00140 -0.0618 0.5690 1.0000
1.750 0.5156 0.00664 0.00143 -0.0617 0.5630 1.0000
2.000 0.5431 0.00670 0.00148 -0.0616 0.5559 1.0000
2.250 0.5704 0.00680 0.00152 -0.0615 0.5481 1.0000
2.500 0.5979 0.00687 0.00158 -0.0614 0.5396 1.0000
2.750 0.6252 0.00696 0.00164 -0.0613 0.5305 1.0000
3.000 0.6524 0.00707 0.00173 -0.0612 0.5206 1.0000
3.250 0.6798 0.00716 0.00181 -0.0611 0.5106 1.0000
3.500 0.7070 0.00727 0.00191 -0.0610 0.5007 1.0000
3.750 0.7341 0.00740 0.00202 -0.0609 0.4891 1.0000
4.000 0.7611 0.00754 0.00215 -0.0607 0.4754 1.0000
4.250 0.7880 0.00770 0.00228 -0.0606 0.4597 1.0000
4.500 0.8146 0.00788 0.00243 -0.0604 0.4408 1.0000
4.750 0.8396 0.00824 0.00262 -0.0601 0.3987 1.0000
5.000 0.8599 0.00922 0.00309 -0.0593 0.2919 1.0000
5.250 0.8795 0.01034 0.00370 -0.0585 0.1949 1.0000
5.500 0.9016 0.01112 0.00419 -0.0579 0.1385 1.0000
5.750 0.9247 0.01173 0.00463 -0.0574 0.1021 1.0000
6.000 0.9462 0.01253 0.00518 -0.0568 0.0588 1.0000
6.250 0.9683 0.01323 0.00576 -0.0561 0.0298 1.0000
6.500 0.9895 0.01403 0.00642 -0.0553 0.0098 1.0000
6.750 1.0132 0.01449 0.00693 -0.0548 0.0078 1.0000
7.000 1.0366 0.01496 0.00746 -0.0542 0.0072 1.0000
7.250 1.0595 0.01548 0.00805 -0.0536 0.0066 1.0000
7.500 1.0817 0.01604 0.00869 -0.0529 0.0062 1.0000
7.750 1.1026 0.01673 0.00948 -0.0520 0.0058 1.0000
8.000 1.1217 0.01758 0.01043 -0.0509 0.0054 1.0000
8.250 1.1391 0.01855 0.01151 -0.0496 0.0052 1.0000
8.500 1.1540 0.01968 0.01274 -0.0479 0.0050 1.0000
8.750 1.1703 0.02060 0.01375 -0.0465 0.0049 1.0000
9.000 1.1847 0.02161 0.01486 -0.0449 0.0049 1.0000
9.250 1.1977 0.02268 0.01601 -0.0431 0.0048 1.0000
9.500 1.2098 0.02362 0.01704 -0.0412 0.0047 1.0000
9.750 1.2186 0.02466 0.01820 -0.0388 0.0046 1.0000
10.000 1.2275 0.02574 0.01937 -0.0367 0.0044 1.0000
10.250 1.2352 0.02699 0.02072 -0.0347 0.0043 1.0000
10.500 1.2426 0.02835 0.02219 -0.0329 0.0041 1.0000
10.750 1.2491 0.02991 0.02386 -0.0313 0.0041 1.0000
11.000 1.2551 0.03163 0.02571 -0.0298 0.0040 1.0000
11.250 1.2608 0.03344 0.02764 -0.0285 0.0039 1.0000
11.500 1.2658 0.03541 0.02974 -0.0273 0.0039 1.0000
11.750 1.2701 0.03752 0.03200 -0.0263 0.0038 1.0000
12.000 1.2741 0.03971 0.03432 -0.0255 0.0037 1.0000
12.250 1.2763 0.04216 0.03693 -0.0248 0.0037 1.0000
12.500 1.2776 0.04478 0.03971 -0.0243 0.0036 1.0000
12.750 1.2769 0.04774 0.04284 -0.0240 0.0036 1.0000
13.000 1.2756 0.05079 0.04604 -0.0240 0.0035 1.0000
13.250 1.2732 0.05404 0.04945 -0.0243 0.0034 1.0000
13.500 1.2677 0.05791 0.05351 -0.0247 0.0035 1.0000
13.750 1.2619 0.06187 0.05761 -0.0256 0.0034 1.0000
14.000 1.2532 0.06644 0.06238 -0.0267 0.0034 1.0000
14.250 1.2442 0.07128 0.06738 -0.0284 0.0033 1.0000
14.500 1.2348 0.07641 0.07267 -0.0304 0.0033 1.0000
14.750 1.2232 0.08226 0.07869 -0.0330 0.0033 1.0000
15.000 1.2103 0.08871 0.08532 -0.0361 0.0033 1.0000
15.250 1.1965 0.09568 0.09245 -0.0397 0.0033 1.0000
15.500 1.1791 0.10390 0.10087 -0.0442 0.0033 1.0000
15.750 1.1637 0.11214 0.10927 -0.0489 0.0033 1.0000
16.000 1.1457 0.12149 0.11879 -0.0545 0.0033 1.0000
16.250 1.1262 0.13185 0.12932 -0.0607 0.0034 1.0000
16.500 1.1022 0.14434 0.14199 -0.0682 0.0035 1.0000
16.750 1.0701 0.16062 0.15845 -0.0776 0.0036 1.0000
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Polar data table (+)
Polar graphs
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