E178 (8.69%) (e178-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: E178 (8.69%) (e178-il) Reynolds number: 100,000 Max Cl/Cd: 56.3 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e178-il-100000.txt Download as CSV file: xf-e178-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E178 (8.69%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3760 0.10954 0.10522 -0.0088 1.0000 0.0829
-9.500 -0.3866 0.10697 0.10272 -0.0127 1.0000 0.0839
-9.250 -0.3977 0.10423 0.10005 -0.0167 1.0000 0.0843
-9.000 -0.3624 0.09717 0.09291 -0.0118 1.0000 0.0892
-8.750 -0.3592 0.09349 0.08926 -0.0129 1.0000 0.0930
-8.500 -0.3662 0.09020 0.08604 -0.0160 1.0000 0.0965
-8.250 -0.3836 0.08746 0.08340 -0.0213 1.0000 0.0977
-8.000 -0.3624 0.08155 0.07749 -0.0185 1.0000 0.1009
-7.750 -0.3542 0.07784 0.07381 -0.0186 1.0000 0.1053
-7.500 -0.3618 0.07434 0.07040 -0.0217 1.0000 0.1096
-7.250 -0.4318 0.08082 0.07663 -0.0212 1.0000 0.1029
-7.000 -0.4269 0.07720 0.07305 -0.0248 1.0000 0.1081
-6.750 -0.4287 0.07202 0.06785 -0.0349 1.0000 0.1129
-6.500 -0.4137 0.06907 0.06499 -0.0310 1.0000 0.1172
-6.250 -0.4111 0.06455 0.06032 -0.0397 1.0000 0.1264
-6.000 -0.3983 0.06161 0.05755 -0.0359 1.0000 0.1305
-5.750 -0.4078 0.05926 0.05503 -0.0386 1.0000 0.1402
-5.500 -0.4148 0.05738 0.05332 -0.0337 1.0000 0.1418
-5.250 -0.4184 0.05587 0.05187 -0.0305 0.9995 0.1453
-5.000 -0.3820 0.05138 0.04720 -0.0372 0.9893 0.1707
-4.750 -0.3453 0.04748 0.04313 -0.0426 0.9801 0.1978
-4.500 -0.2862 0.03292 0.02664 -0.0526 0.9715 0.0797
-4.250 -0.2454 0.02820 0.02088 -0.0548 0.9631 0.0689
-4.000 -0.2013 0.02509 0.01717 -0.0578 0.9569 0.0684
-3.750 -0.1628 0.02293 0.01451 -0.0597 0.9480 0.0729
-3.500 -0.1193 0.02091 0.01228 -0.0624 0.9419 0.0759
-3.250 -0.0846 0.01960 0.01081 -0.0633 0.9319 0.0817
-3.000 -0.0506 0.01836 0.00961 -0.0643 0.9229 0.0943
-2.750 -0.0177 0.01703 0.00847 -0.0650 0.9147 0.1338
-2.500 0.0024 0.01501 0.00781 -0.0639 0.9040 0.3868
-2.250 0.0892 0.01298 0.00740 -0.0719 0.9054 0.9837
-2.000 0.1303 0.01297 0.00698 -0.0748 0.8959 1.0000
-1.750 0.1543 0.01311 0.00684 -0.0742 0.8851 1.0000
-1.500 0.1767 0.01329 0.00679 -0.0732 0.8741 1.0000
-1.250 0.1987 0.01352 0.00682 -0.0723 0.8633 1.0000
-1.000 0.2213 0.01375 0.00686 -0.0713 0.8535 1.0000
-0.750 0.2443 0.01394 0.00685 -0.0702 0.8452 1.0000
-0.500 0.2669 0.01423 0.00701 -0.0694 0.8351 1.0000
-0.250 0.2899 0.01449 0.00714 -0.0685 0.8265 1.0000
0.000 0.3133 0.01473 0.00725 -0.0675 0.8185 1.0000
0.250 0.3367 0.01506 0.00748 -0.0669 0.8094 1.0000
0.500 0.3606 0.01529 0.00761 -0.0659 0.8025 1.0000
0.750 0.3844 0.01564 0.00790 -0.0654 0.7934 1.0000
1.000 0.4084 0.01596 0.00816 -0.0647 0.7857 1.0000
1.250 0.4327 0.01625 0.00841 -0.0640 0.7779 1.0000
1.500 0.4568 0.01663 0.00877 -0.0635 0.7696 1.0000
1.750 0.4814 0.01688 0.00897 -0.0626 0.7627 1.0000
2.000 0.5055 0.01732 0.00942 -0.0622 0.7536 1.0000
2.250 0.5305 0.01751 0.00959 -0.0612 0.7475 1.0000
2.500 0.5543 0.01795 0.01009 -0.0608 0.7375 1.0000
2.750 0.5785 0.01830 0.01045 -0.0601 0.7288 1.0000
3.000 0.6035 0.01845 0.01061 -0.0590 0.7208 1.0000
3.250 0.6273 0.01884 0.01106 -0.0584 0.7103 1.0000
3.500 0.6516 0.01910 0.01141 -0.0575 0.7010 1.0000
3.750 0.6770 0.01914 0.01147 -0.0563 0.6924 1.0000
4.000 0.7010 0.01939 0.01181 -0.0554 0.6807 1.0000
4.250 0.7252 0.01954 0.01204 -0.0543 0.6690 1.0000
4.500 0.7497 0.01959 0.01221 -0.0531 0.6570 1.0000
4.750 0.7745 0.01954 0.01224 -0.0517 0.6444 1.0000
5.000 0.7994 0.01943 0.01222 -0.0504 0.6309 1.0000
5.250 0.8243 0.01927 0.01216 -0.0489 0.6161 1.0000
5.500 0.8493 0.01901 0.01199 -0.0474 0.5999 1.0000
5.750 0.8748 0.01860 0.01170 -0.0458 0.5824 1.0000
6.000 0.8990 0.01829 0.01153 -0.0443 0.5608 1.0000
6.250 0.9236 0.01785 0.01119 -0.0426 0.5365 1.0000
6.500 0.9467 0.01751 0.01100 -0.0409 0.5041 1.0000
6.750 0.9685 0.01725 0.01080 -0.0390 0.4581 1.0000
7.000 0.9858 0.01751 0.01090 -0.0368 0.3747 1.0000
7.250 0.9932 0.01923 0.01179 -0.0341 0.2532 1.0000
7.500 0.9978 0.02164 0.01347 -0.0318 0.1637 1.0000
7.750 1.0014 0.02421 0.01544 -0.0293 0.1031 1.0000
8.000 1.0077 0.02664 0.01763 -0.0266 0.0688 1.0000
8.250 1.0186 0.02882 0.01968 -0.0245 0.0550 1.0000
8.500 1.0373 0.03134 0.02222 -0.0228 0.0486 1.0000
8.750 1.0575 0.03344 0.02435 -0.0217 0.0434 1.0000
9.000 1.0795 0.03647 0.02750 -0.0210 0.0393 1.0000
9.250 1.1006 0.03929 0.03073 -0.0198 0.0377 1.0000
9.500 1.1179 0.04266 0.03451 -0.0185 0.0370 1.0000
9.750 1.1295 0.04634 0.03863 -0.0169 0.0370 1.0000
10.000 1.1353 0.05025 0.04299 -0.0150 0.0373 1.0000
10.250 1.1360 0.05430 0.04744 -0.0131 0.0378 1.0000
10.500 1.1317 0.05841 0.05191 -0.0112 0.0384 1.0000
10.750 1.1230 0.06236 0.05613 -0.0093 0.0390 1.0000
11.000 1.1102 0.06629 0.06028 -0.0075 0.0395 1.0000
11.250 1.0962 0.07073 0.06491 -0.0066 0.0400 1.0000
11.500 1.0936 0.07588 0.07020 -0.0064 0.0412 1.0000
11.750 1.0739 0.07877 0.07335 -0.0065 0.0418 1.0000
12.000 1.0438 0.08381 0.07867 -0.0087 0.0425 1.0000
12.250 1.0119 0.09053 0.08561 -0.0129 0.0429 1.0000
12.500 0.9767 0.09941 0.09467 -0.0193 0.0435 1.0000
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Polar data table (+)
Polar graphs
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