Coanda 1 (coanda1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 1 (coanda1-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.53 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda1-il-1000000.txt Download as CSV file: xf-coanda1-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4446 0.08542 0.08390 -0.0142 1.0000 0.0077
-7.750 -0.4565 0.08260 0.08112 -0.0130 1.0000 0.0077
-7.500 -0.4593 0.07938 0.07792 -0.0131 1.0000 0.0077
-7.250 -0.4611 0.07575 0.07429 -0.0138 1.0000 0.0078
-7.000 -0.4613 0.07227 0.07082 -0.0144 1.0000 0.0078
-6.750 -0.4746 0.06439 0.06294 -0.0170 0.9998 0.0082
-6.500 -0.4492 0.05837 0.05682 -0.0241 0.9975 0.0087
-6.250 -0.4211 0.05410 0.05247 -0.0292 0.9954 0.0092
-6.000 -0.3938 0.04997 0.04825 -0.0334 0.9934 0.0098
-5.750 -0.3682 0.04678 0.04498 -0.0361 0.9907 0.0113
-5.500 -0.3410 0.04168 0.03973 -0.0392 0.9875 0.0125
-4.750 -0.2905 0.01556 0.01160 -0.0373 0.9744 0.0082
-4.500 -0.2618 0.01395 0.00976 -0.0373 0.9725 0.0075
-4.250 -0.2325 0.01219 0.00768 -0.0374 0.9710 0.0074
-4.000 -0.2004 0.01117 0.00647 -0.0381 0.9699 0.0076
-3.750 -0.1754 0.00985 0.00491 -0.0371 0.9666 0.0085
-3.500 -0.1480 0.00905 0.00395 -0.0368 0.9629 0.0102
-3.250 -0.1157 0.00859 0.00343 -0.0376 0.9605 0.0112
-3.000 -0.0805 0.00814 0.00290 -0.0390 0.9583 0.0130
-2.750 -0.0424 0.00775 0.00241 -0.0411 0.9561 0.0149
-2.500 -0.0155 0.00739 0.00199 -0.0406 0.9477 0.0219
-2.250 0.0257 0.00775 0.00262 -0.0433 0.9410 0.0653
-2.000 0.0618 0.00782 0.00267 -0.0451 0.9299 0.0678
-1.750 0.0975 0.00807 0.00291 -0.0467 0.9159 0.0708
-1.500 0.1289 0.00802 0.00281 -0.0474 0.8973 0.0722
-1.250 0.1576 0.00844 0.00315 -0.0474 0.8728 0.0759
-1.000 0.1834 0.00829 0.00288 -0.0467 0.8412 0.0765
-0.750 0.2067 0.00820 0.00263 -0.0456 0.7989 0.0770
-0.500 0.2288 0.00827 0.00253 -0.0441 0.7580 0.0777
-0.250 0.2513 0.00834 0.00245 -0.0428 0.7239 0.0783
0.000 0.2745 0.00836 0.00236 -0.0417 0.6947 0.0787
0.250 0.2970 0.00799 0.00190 -0.0406 0.6658 0.0811
0.500 0.3201 0.00796 0.00178 -0.0396 0.6350 0.0820
0.750 0.3430 0.00800 0.00171 -0.0385 0.6015 0.0831
1.000 0.3665 0.00805 0.00169 -0.0375 0.5732 0.0841
1.250 0.3903 0.00809 0.00165 -0.0367 0.5471 0.0849
1.500 0.4143 0.00814 0.00163 -0.0358 0.5231 0.0856
1.750 0.4343 0.00843 0.00163 -0.0342 0.4472 0.0861
2.000 0.4536 0.00885 0.00168 -0.0326 0.3530 0.0866
2.250 0.4748 0.00916 0.00177 -0.0314 0.2938 0.0871
2.500 0.4976 0.00937 0.00182 -0.0304 0.2517 0.0876
2.750 0.5189 0.00972 0.00192 -0.0292 0.1926 0.0883
3.000 0.5403 0.01007 0.00204 -0.0281 0.1441 0.0888
3.250 0.5582 0.01075 0.00231 -0.0263 0.0531 0.0896
3.500 0.5806 0.01107 0.00249 -0.0252 0.0158 0.0906
3.750 0.6051 0.01122 0.00274 -0.0245 0.0141 0.0916
4.000 0.6289 0.01131 0.00290 -0.0237 0.0130 0.0951
4.250 0.6521 0.01157 0.00326 -0.0227 0.0111 0.0974
4.500 0.6731 0.01208 0.00389 -0.0212 0.0096 0.1004
4.750 0.6941 0.01258 0.00448 -0.0198 0.0094 0.1023
5.000 0.7136 0.01325 0.00525 -0.0181 0.0093 0.1040
5.250 0.7350 0.01367 0.00574 -0.0168 0.0088 0.1072
5.500 0.7562 0.01409 0.00624 -0.0155 0.0085 0.1129
5.750 0.8832 0.01459 0.00870 -0.0389 0.0065 0.9887
17.000 0.6538 0.17984 0.17832 -0.0351 0.0048 1.0000
17.250 0.6545 0.18322 0.18170 -0.0362 0.0048 1.0000
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Polar data table (+)
Polar graphs
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