E176 (8.83%) (e176-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 200,000 Max Cl/Cd: 78.42 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e176-il-200000-n5.txt Download as CSV file: xf-e176-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3968 0.08592 0.08265 -0.0262 1.0000 0.0269
-8.000 -0.3925 0.08291 0.07969 -0.0272 1.0000 0.0275
-7.750 -0.3928 0.07932 0.07616 -0.0292 1.0000 0.0274
-7.500 -0.3953 0.07499 0.07190 -0.0329 1.0000 0.0270
-7.250 -0.3856 0.07337 0.07031 -0.0332 1.0000 0.0302
-7.000 -0.3676 0.06253 0.05936 -0.0492 0.9652 0.0250
-6.750 -0.3495 0.05814 0.05490 -0.0534 0.9372 0.0231
-6.250 -0.3150 0.03963 0.03550 -0.0661 0.8850 0.0174
-6.000 -0.2997 0.03504 0.03052 -0.0672 0.8659 0.0171
-5.750 -0.2819 0.03100 0.02602 -0.0677 0.8495 0.0168
-5.500 -0.2620 0.02748 0.02197 -0.0676 0.8350 0.0166
-5.250 -0.2401 0.02459 0.01852 -0.0673 0.8220 0.0165
-5.000 -0.2166 0.02222 0.01564 -0.0669 0.8101 0.0165
-4.750 -0.1919 0.02036 0.01333 -0.0664 0.7991 0.0167
-4.500 -0.1664 0.01887 0.01147 -0.0659 0.7885 0.0170
-4.250 -0.1404 0.01767 0.00998 -0.0654 0.7783 0.0173
-4.000 -0.1143 0.01666 0.00873 -0.0650 0.7690 0.0179
-3.750 -0.0889 0.01555 0.00749 -0.0647 0.7601 0.0197
-3.500 -0.0625 0.01483 0.00664 -0.0643 0.7514 0.0206
-3.250 -0.0362 0.01417 0.00583 -0.0639 0.7435 0.0212
-3.000 -0.0094 0.01361 0.00516 -0.0637 0.7352 0.0219
-2.750 0.0175 0.01317 0.00458 -0.0634 0.7280 0.0229
-2.500 0.0447 0.01281 0.00407 -0.0631 0.7204 0.0245
-2.250 0.0719 0.01247 0.00363 -0.0629 0.7136 0.0280
-2.000 0.0992 0.01211 0.00329 -0.0627 0.7065 0.0445
-1.750 0.1255 0.01157 0.00306 -0.0627 0.7002 0.1276
-1.500 0.1518 0.01106 0.00292 -0.0627 0.6933 0.2370
-1.250 0.1780 0.01070 0.00280 -0.0625 0.6876 0.3343
-1.000 0.2009 0.00990 0.00282 -0.0618 0.6809 0.5592
-0.750 0.2196 0.00919 0.00284 -0.0593 0.6754 0.7863
-0.500 0.2685 0.00889 0.00269 -0.0629 0.6692 0.9793
-0.250 0.3005 0.00894 0.00260 -0.0638 0.6631 1.0000
0.000 0.3271 0.00902 0.00255 -0.0635 0.6576 1.0000
0.250 0.3540 0.00910 0.00253 -0.0633 0.6514 1.0000
0.500 0.3808 0.00920 0.00251 -0.0631 0.6462 1.0000
0.750 0.4079 0.00928 0.00253 -0.0629 0.6401 1.0000
1.000 0.4349 0.00938 0.00255 -0.0627 0.6345 1.0000
1.250 0.4620 0.00949 0.00259 -0.0626 0.6291 1.0000
1.500 0.4892 0.00959 0.00266 -0.0624 0.6230 1.0000
1.750 0.5162 0.00970 0.00270 -0.0622 0.6179 1.0000
2.000 0.5435 0.00981 0.00282 -0.0621 0.6115 1.0000
2.250 0.5706 0.00992 0.00290 -0.0620 0.6057 1.0000
2.500 0.5977 0.01004 0.00301 -0.0618 0.5995 1.0000
2.750 0.6247 0.01015 0.00312 -0.0617 0.5925 1.0000
3.000 0.6517 0.01027 0.00325 -0.0615 0.5849 1.0000
3.250 0.6786 0.01038 0.00336 -0.0613 0.5769 1.0000
3.500 0.7055 0.01049 0.00350 -0.0611 0.5675 1.0000
3.750 0.7322 0.01061 0.00363 -0.0608 0.5579 1.0000
4.000 0.7588 0.01073 0.00378 -0.0606 0.5479 1.0000
4.250 0.7854 0.01085 0.00396 -0.0603 0.5368 1.0000
4.500 0.8119 0.01098 0.00413 -0.0601 0.5248 1.0000
4.750 0.8382 0.01112 0.00431 -0.0597 0.5113 1.0000
5.000 0.8642 0.01128 0.00453 -0.0594 0.4959 1.0000
5.250 0.8900 0.01146 0.00473 -0.0590 0.4785 1.0000
5.500 0.9152 0.01167 0.00496 -0.0585 0.4542 1.0000
5.750 0.9379 0.01205 0.00517 -0.0577 0.4017 1.0000
6.000 0.9568 0.01287 0.00557 -0.0565 0.3183 1.0000
6.250 0.9740 0.01400 0.00630 -0.0554 0.2376 1.0000
6.500 0.9894 0.01538 0.00718 -0.0542 0.1547 1.0000
6.750 1.0071 0.01648 0.00799 -0.0531 0.1025 1.0000
7.000 1.0240 0.01764 0.00888 -0.0520 0.0583 1.0000
7.500 1.0584 0.01980 0.01085 -0.0495 0.0167 1.0000
7.750 1.0764 0.02074 0.01188 -0.0483 0.0140 1.0000
8.000 1.0937 0.02169 0.01293 -0.0470 0.0123 1.0000
8.250 1.1109 0.02258 0.01395 -0.0458 0.0111 1.0000
8.500 1.1263 0.02360 0.01509 -0.0443 0.0103 1.0000
8.750 1.1395 0.02473 0.01636 -0.0426 0.0098 1.0000
9.000 1.1498 0.02601 0.01776 -0.0407 0.0094 1.0000
9.250 1.1566 0.02731 0.01918 -0.0383 0.0092 1.0000
9.500 1.1605 0.02889 0.02087 -0.0357 0.0089 1.0000
9.750 1.1635 0.03070 0.02279 -0.0335 0.0087 1.0000
10.000 1.1672 0.03268 0.02486 -0.0316 0.0086 1.0000
10.250 1.1746 0.03444 0.02680 -0.0301 0.0085 1.0000
10.500 1.1824 0.03632 0.02882 -0.0287 0.0084 1.0000
10.750 1.1904 0.03830 0.03093 -0.0274 0.0084 1.0000
11.000 1.1984 0.04038 0.03318 -0.0263 0.0083 1.0000
11.250 1.2055 0.04270 0.03569 -0.0251 0.0082 1.0000
11.500 1.2113 0.04514 0.03832 -0.0241 0.0082 1.0000
11.750 1.2151 0.04784 0.04125 -0.0233 0.0081 1.0000
12.000 1.2167 0.05076 0.04439 -0.0226 0.0081 1.0000
12.250 1.2155 0.05395 0.04783 -0.0222 0.0080 1.0000
12.500 1.2120 0.05743 0.05155 -0.0221 0.0079 1.0000
12.750 1.2062 0.06129 0.05566 -0.0223 0.0078 1.0000
13.000 1.1984 0.06544 0.06005 -0.0230 0.0077 1.0000
13.250 1.1892 0.06991 0.06475 -0.0242 0.0075 1.0000
13.500 1.1775 0.07506 0.07013 -0.0258 0.0076 1.0000
13.750 1.1640 0.08065 0.07594 -0.0281 0.0074 1.0000
14.000 1.1493 0.08683 0.08233 -0.0309 0.0075 1.0000
14.250 1.1335 0.09363 0.08934 -0.0343 0.0075 1.0000
14.500 1.1172 0.10107 0.09698 -0.0385 0.0075 1.0000
14.750 1.0995 0.10944 0.10554 -0.0435 0.0075 1.0000
15.000 1.0814 0.11855 0.11482 -0.0491 0.0076 1.0000
15.250 1.0622 0.12883 0.12526 -0.0556 0.0078 1.0000
15.500 1.0433 0.13979 0.13634 -0.0624 0.0081 1.0000
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Polar data table (+)
Polar graphs
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