Coanda 1 (coanda1-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 1 (coanda1-il) Reynolds number: 500,000 Max Cl/Cd: 51.31 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda1-il-500000-n5.txt Download as CSV file: xf-coanda1-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 1
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4331 0.08739 0.08527 -0.0149 1.0000 0.0038
-7.750 -0.4388 0.08479 0.08272 -0.0146 1.0000 0.0042
-7.500 -0.4467 0.08211 0.08008 -0.0136 1.0000 0.0039
-7.250 -0.4487 0.07870 0.07670 -0.0142 1.0000 0.0035
-7.000 -0.4473 0.07576 0.07377 -0.0148 1.0000 0.0047
-6.750 -0.4475 0.07219 0.07021 -0.0153 1.0000 0.0040
-6.500 -0.4305 0.06736 0.06535 -0.0200 0.9983 0.0053
-6.250 -0.4026 0.06126 0.05917 -0.0274 0.9949 0.0054
-6.000 -0.3775 0.05507 0.05290 -0.0332 0.9906 0.0054
-5.750 -0.3493 0.04881 0.04649 -0.0388 0.9869 0.0052
-5.500 -0.3261 0.04222 0.03970 -0.0421 0.9812 0.0050
-5.250 -0.3019 0.03421 0.03135 -0.0449 0.9769 0.0049
-5.000 -0.2893 0.02554 0.02207 -0.0435 0.9693 0.0047
-4.750 -0.2680 0.01971 0.01557 -0.0426 0.9661 0.0046
-4.500 -0.2490 0.01708 0.01242 -0.0405 0.9603 0.0045
-4.250 -0.2234 0.01512 0.01005 -0.0398 0.9566 0.0044
-4.000 -0.1945 0.01362 0.00823 -0.0397 0.9542 0.0044
-3.750 -0.1694 0.01240 0.00677 -0.0386 0.9494 0.0044
-3.500 -0.1420 0.01161 0.00584 -0.0382 0.9449 0.0044
-3.250 -0.1099 0.01105 0.00512 -0.0387 0.9416 0.0047
-3.000 -0.0774 0.01049 0.00437 -0.0394 0.9380 0.0056
-2.750 -0.0480 0.01005 0.00384 -0.0397 0.9320 0.0132
-2.500 -0.0144 0.00936 0.00297 -0.0410 0.9280 0.0194
-2.250 0.0187 0.00905 0.00258 -0.0420 0.9197 0.0207
-2.000 0.0557 0.00880 0.00226 -0.0439 0.9095 0.0211
-1.750 0.0918 0.00860 0.00199 -0.0457 0.8940 0.0229
-1.500 0.1259 0.00830 0.00174 -0.0470 0.8696 0.0474
-1.250 0.1564 0.00833 0.00171 -0.0474 0.8355 0.0604
-1.000 0.1826 0.00840 0.00150 -0.0468 0.7871 0.0621
-0.750 0.2051 0.00858 0.00147 -0.0454 0.7365 0.0642
-0.500 0.2272 0.00878 0.00149 -0.0441 0.6948 0.0661
-0.250 0.2502 0.00893 0.00150 -0.0429 0.6593 0.0683
0.000 0.2735 0.00903 0.00150 -0.0419 0.6290 0.0701
0.250 0.2969 0.00916 0.00152 -0.0409 0.5992 0.0720
0.500 0.3205 0.00933 0.00158 -0.0400 0.5700 0.0736
0.750 0.3440 0.00945 0.00164 -0.0391 0.5421 0.0774
1.000 0.3685 0.00959 0.00174 -0.0384 0.5196 0.0801
1.250 0.3925 0.00965 0.00175 -0.0377 0.4978 0.0818
1.500 0.4164 0.00972 0.00175 -0.0369 0.4731 0.0830
1.750 0.4400 0.00982 0.00179 -0.0360 0.4409 0.0842
2.000 0.4597 0.01021 0.00185 -0.0345 0.3595 0.0852
2.250 0.4799 0.01065 0.00198 -0.0332 0.2892 0.0863
2.500 0.5028 0.01089 0.00209 -0.0323 0.2521 0.0871
2.750 0.5257 0.01112 0.00219 -0.0315 0.2156 0.0878
3.000 0.5489 0.01127 0.00228 -0.0306 0.1904 0.0897
3.250 0.5724 0.01145 0.00240 -0.0299 0.1715 0.0913
3.500 0.5956 0.01166 0.00264 -0.0291 0.1502 0.0930
3.750 0.6173 0.01203 0.00284 -0.0281 0.1098 0.0946
4.000 0.6328 0.01308 0.00350 -0.0258 0.0067 0.0963
4.250 0.6556 0.01340 0.00393 -0.0248 0.0035 0.0984
4.500 0.6783 0.01377 0.00443 -0.0237 0.0028 0.1003
4.750 0.6996 0.01427 0.00509 -0.0224 0.0026 0.1040
5.000 0.7194 0.01496 0.00590 -0.0207 0.0025 0.1090
5.250 0.7381 0.01571 0.00676 -0.0189 0.0025 0.1147
5.500 0.7559 0.01649 0.00766 -0.0169 0.0025 0.1308
5.750 0.8539 0.01814 0.01122 -0.0337 0.0026 0.9838
6.000 0.8907 0.01999 0.01323 -0.0358 0.0027 0.9891
6.250 0.9268 0.02185 0.01521 -0.0379 0.0028 0.9930
6.500 0.9704 0.02438 0.01795 -0.0415 0.0029 0.9971
6.750 1.0075 0.02714 0.02096 -0.0440 0.0031 1.0000
7.000 1.0215 0.03002 0.02408 -0.0415 0.0033 1.0000
7.250 1.0338 0.03471 0.02895 -0.0394 0.0035 1.0000
7.500 1.0464 0.03701 0.03147 -0.0369 0.0035 1.0000
7.750 1.0573 0.03874 0.03341 -0.0343 0.0036 1.0000
8.000 1.0652 0.04092 0.03583 -0.0314 0.0036 1.0000
8.250 1.0681 0.04385 0.03903 -0.0280 0.0036 1.0000
8.500 1.0673 0.04705 0.04251 -0.0243 0.0036 1.0000
8.750 1.0694 0.04893 0.04463 -0.0210 0.0036 1.0000
9.250 1.0465 0.05633 0.05251 -0.0125 0.0035 1.0000
9.500 1.0352 0.05913 0.05549 -0.0085 0.0035 1.0000
9.750 1.0163 0.06094 0.05742 -0.0032 0.0035 1.0000
10.000 0.9984 0.06334 0.05996 0.0007 0.0035 1.0000
10.250 0.9802 0.06617 0.06292 0.0030 0.0035 1.0000
10.500 0.9625 0.06949 0.06638 0.0037 0.0035 1.0000
10.750 0.9476 0.07332 0.07034 0.0031 0.0035 1.0000
11.000 0.9305 0.07816 0.07531 0.0009 0.0035 1.0000
11.250 0.9155 0.08349 0.08076 -0.0023 0.0035 1.0000
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Polar data table (+)
Polar graphs
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