E184 (8.33%) (e184-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E184 (8.33%) (e184-il) Reynolds number: 50,000 Max Cl/Cd: 30.86 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e184-il-50000.txt Download as CSV file: xf-e184-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E184 (8.33%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6625 0.14376 0.13753 0.0399 1.0000 0.1802
-10.500 -0.6333 0.13638 0.13008 0.0419 1.0000 0.1899
-10.250 -0.6529 0.13563 0.12946 0.0374 1.0000 0.1942
-10.000 -0.6299 0.12946 0.12325 0.0388 1.0000 0.2063
-9.750 -0.6189 0.12486 0.11866 0.0387 1.0000 0.2164
-9.500 -0.6390 0.12373 0.11766 0.0346 1.0000 0.2222
-9.250 -0.6254 0.11896 0.11288 0.0351 1.0000 0.2357
-9.000 -0.6101 0.11404 0.10796 0.0355 1.0000 0.2476
-8.750 -0.6018 0.10981 0.10376 0.0351 1.0000 0.2576
-8.500 -0.6008 0.10620 0.10021 0.0340 1.0000 0.2686
-8.000 -0.6002 0.09939 0.09354 0.0323 1.0000 0.2946
-7.500 -0.5838 0.09168 0.08586 0.0325 1.0000 0.3247
-7.250 -0.5750 0.08793 0.08214 0.0327 1.0000 0.3413
-7.000 -0.5778 0.08504 0.07934 0.0326 1.0000 0.3616
-6.750 -0.5702 0.08121 0.07557 0.0332 1.0000 0.3803
-6.000 -0.5829 0.05184 0.04496 -0.0079 1.0000 0.1351
-5.750 -0.5656 0.04628 0.03878 -0.0087 1.0000 0.1213
-5.500 -0.5468 0.04143 0.03323 -0.0087 1.0000 0.1132
-5.250 -0.5246 0.03794 0.02898 -0.0081 1.0000 0.1102
-5.000 -0.5015 0.03473 0.02552 -0.0079 1.0000 0.1136
-4.750 -0.4766 0.03205 0.02254 -0.0076 1.0000 0.1173
-4.500 -0.4500 0.02940 0.01944 -0.0071 1.0000 0.1198
-4.250 -0.4224 0.02715 0.01666 -0.0065 1.0000 0.1246
-4.000 -0.3954 0.02497 0.01450 -0.0062 1.0000 0.1362
-3.750 -0.3714 0.02319 0.01283 -0.0055 1.0000 0.1623
-3.500 -0.3473 0.02094 0.01097 -0.0046 1.0000 0.2331
-3.250 -0.1651 0.01699 0.00929 -0.0211 1.0000 1.0000
-3.000 -0.1450 0.01650 0.00843 -0.0222 1.0000 1.0000
-2.750 -0.1238 0.01621 0.00786 -0.0230 1.0000 1.0000
-2.500 -0.1048 0.01609 0.00748 -0.0233 1.0000 1.0000
-2.250 -0.0930 0.01612 0.00732 -0.0223 1.0000 1.0000
-2.000 -0.0932 0.01634 0.00736 -0.0191 1.0000 1.0000
-1.750 -0.0941 0.01660 0.00740 -0.0157 1.0000 1.0000
-1.500 -0.0921 0.01686 0.00747 -0.0126 1.0000 1.0000
-1.250 -0.0873 0.01713 0.00756 -0.0099 1.0000 1.0000
-1.000 -0.0801 0.01742 0.00766 -0.0076 1.0000 1.0000
-0.750 -0.0713 0.01772 0.00779 -0.0055 1.0000 1.0000
-0.500 -0.0612 0.01804 0.00796 -0.0037 1.0000 1.0000
-0.250 -0.0498 0.01839 0.00815 -0.0021 1.0000 1.0000
0.000 -0.0353 0.01877 0.00841 -0.0011 0.9992 1.0000
0.250 0.0087 0.01942 0.00891 -0.0057 0.9883 1.0000
0.500 0.0518 0.02011 0.00951 -0.0101 0.9775 1.0000
0.750 0.0950 0.02083 0.01018 -0.0144 0.9668 1.0000
1.000 0.1398 0.02159 0.01092 -0.0190 0.9559 1.0000
1.250 0.1783 0.02231 0.01164 -0.0222 0.9445 1.0000
1.500 0.2146 0.02306 0.01241 -0.0250 0.9326 1.0000
1.750 0.2515 0.02384 0.01326 -0.0279 0.9203 1.0000
2.000 0.2892 0.02463 0.01415 -0.0307 0.9074 1.0000
2.250 0.3272 0.02544 0.01506 -0.0334 0.8936 1.0000
2.500 0.3660 0.02623 0.01604 -0.0362 0.8788 1.0000
2.750 0.4038 0.02700 0.01698 -0.0383 0.8630 1.0000
3.000 0.4432 0.02774 0.01792 -0.0403 0.8461 1.0000
3.250 0.4648 0.02855 0.01888 -0.0394 0.8271 1.0000
3.500 0.4990 0.02914 0.01974 -0.0397 0.8068 1.0000
3.750 0.5231 0.02978 0.02058 -0.0384 0.7849 1.0000
4.000 0.5549 0.02998 0.02103 -0.0367 0.7619 1.0000
4.250 0.5770 0.03020 0.02148 -0.0338 0.7362 1.0000
4.500 0.5985 0.03012 0.02167 -0.0299 0.7089 1.0000
4.750 0.6194 0.02962 0.02141 -0.0251 0.6801 1.0000
5.000 0.6395 0.02858 0.02058 -0.0192 0.6501 1.0000
5.500 0.6745 0.02557 0.01796 -0.0064 0.5687 1.0000
5.750 0.6908 0.02327 0.01576 0.0010 0.4992 1.0000
6.000 0.7006 0.02270 0.01417 0.0077 0.3448 1.0000
6.250 0.7074 0.02598 0.01611 0.0106 0.2130 1.0000
6.500 0.7207 0.02906 0.01857 0.0126 0.1426 1.0000
6.750 0.7424 0.03171 0.02103 0.0144 0.1139 1.0000
7.000 0.7662 0.03441 0.02378 0.0158 0.0995 1.0000
7.250 0.7884 0.03737 0.02703 0.0170 0.0907 1.0000
7.500 0.8100 0.04067 0.03077 0.0181 0.0871 1.0000
7.750 0.8289 0.04436 0.03487 0.0191 0.0857 1.0000
8.000 0.8425 0.04857 0.03967 0.0200 0.0862 1.0000
8.250 0.8499 0.05326 0.04497 0.0207 0.0881 1.0000
8.500 0.8522 0.05811 0.05029 0.0210 0.0901 1.0000
8.750 0.8504 0.06298 0.05552 0.0210 0.0919 1.0000
9.000 0.8469 0.06787 0.06062 0.0209 0.0935 1.0000
9.250 0.8484 0.07290 0.06575 0.0208 0.0952 1.0000
9.500 0.7948 0.07902 0.07221 0.0166 0.1014 1.0000
9.750 0.7706 0.08563 0.07882 0.0123 0.1048 1.0000
10.000 0.7833 0.09065 0.08382 0.0131 0.1087 1.0000
10.250 0.7309 0.10302 0.09601 -0.0005 0.1193 1.0000
10.500 0.7090 0.11340 0.10627 -0.0088 0.1433 1.0000
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Polar data table (+)
Polar graphs
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