Coanda 2 (coanda2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 2 (coanda2-il) Reynolds number: 200,000 Max Cl/Cd: 49.48 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda2-il-200000-n5.txt Download as CSV file: xf-coanda2-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 2
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4273 0.09803 0.09454 -0.0165 1.0000 0.0116
-9.000 -0.4268 0.09480 0.09136 -0.0168 1.0000 0.0112
-8.750 -0.4270 0.09167 0.08827 -0.0173 1.0000 0.0109
-8.500 -0.4292 0.08843 0.08509 -0.0177 1.0000 0.0107
-8.250 -0.4333 0.08546 0.08218 -0.0178 1.0000 0.0104
-8.000 -0.4396 0.08279 0.07957 -0.0173 1.0000 0.0102
-7.750 -0.4436 0.07955 0.07638 -0.0176 1.0000 0.0101
-7.500 -0.4450 0.07606 0.07294 -0.0185 1.0000 0.0099
-7.250 -0.4451 0.07235 0.06925 -0.0197 1.0000 0.0097
-7.000 -0.4444 0.06821 0.06513 -0.0211 1.0000 0.0096
-6.750 -0.4417 0.06409 0.06100 -0.0223 1.0000 0.0092
-6.500 -0.4377 0.05961 0.05649 -0.0235 1.0000 0.0090
-6.250 -0.4332 0.05419 0.05099 -0.0247 1.0000 0.0089
-6.000 -0.4272 0.04857 0.04523 -0.0254 1.0000 0.0085
-5.750 -0.4226 0.04101 0.03735 -0.0256 1.0000 0.0082
-5.500 -0.4065 0.02965 0.02512 -0.0274 0.9964 0.0077
-5.250 -0.3822 0.02483 0.01963 -0.0276 0.9927 0.0076
-5.000 -0.3550 0.02218 0.01649 -0.0277 0.9889 0.0080
-4.750 -0.3251 0.02049 0.01440 -0.0281 0.9857 0.0079
-4.500 -0.2960 0.01930 0.01285 -0.0282 0.9808 0.0083
-4.250 -0.2606 0.01835 0.01160 -0.0294 0.9768 0.0093
-4.000 -0.2285 0.01759 0.01058 -0.0299 0.9703 0.0108
-3.750 -0.1921 0.01581 0.00834 -0.0313 0.9660 0.0197
-3.500 -0.1602 0.01537 0.00794 -0.0318 0.9591 0.0604
-3.250 -0.1232 0.01530 0.00770 -0.0335 0.9542 0.0634
-3.000 -0.0933 0.01532 0.00763 -0.0337 0.9481 0.0663
-2.750 -0.0609 0.01522 0.00738 -0.0345 0.9429 0.0701
-2.500 -0.0243 0.01510 0.00699 -0.0362 0.9393 0.0732
-2.250 0.0022 0.01471 0.00656 -0.0358 0.9316 0.0745
-2.000 0.0374 0.01436 0.00619 -0.0372 0.9271 0.0758
-1.750 0.0663 0.01414 0.00595 -0.0374 0.9190 0.0779
-1.500 0.1035 0.01420 0.00596 -0.0392 0.9130 0.0845
-1.250 0.1338 0.01412 0.00578 -0.0395 0.9029 0.0866
-1.000 0.1681 0.01349 0.00511 -0.0408 0.8935 0.0876
-0.750 0.2036 0.01300 0.00464 -0.0423 0.8823 0.0887
-0.500 0.2376 0.01263 0.00431 -0.0435 0.8680 0.0905
-0.250 0.2724 0.01233 0.00403 -0.0448 0.8493 0.0929
0.000 0.3075 0.01203 0.00371 -0.0461 0.8239 0.0945
0.250 0.3426 0.01175 0.00338 -0.0474 0.7868 0.0956
0.500 0.3750 0.01161 0.00308 -0.0481 0.7302 0.0969
0.750 0.4008 0.01170 0.00288 -0.0473 0.6656 0.0979
1.000 0.4228 0.01188 0.00283 -0.0459 0.6157 0.0991
1.250 0.4446 0.01204 0.00285 -0.0446 0.5748 0.1003
1.500 0.4663 0.01210 0.00282 -0.0433 0.5392 0.1020
1.750 0.4884 0.01222 0.00284 -0.0421 0.5056 0.1039
2.000 0.5098 0.01241 0.00290 -0.0407 0.4677 0.1060
2.250 0.5301 0.01271 0.00297 -0.0393 0.4221 0.1082
2.500 0.5528 0.01290 0.00308 -0.0383 0.3945 0.1105
2.750 0.5766 0.01305 0.00329 -0.0375 0.3746 0.1134
3.000 0.6005 0.01318 0.00344 -0.0367 0.3528 0.1191
3.250 0.6243 0.01335 0.00360 -0.0360 0.3279 0.1261
3.500 0.6432 0.01391 0.00379 -0.0345 0.2434 0.1377
3.750 0.7837 0.01584 0.00646 -0.0624 0.0127 1.0000
4.000 0.8066 0.01640 0.00716 -0.0612 0.0118 1.0000
4.250 0.8285 0.01710 0.00802 -0.0599 0.0099 1.0000
4.500 0.8455 0.01837 0.00940 -0.0581 0.0072 1.0000
4.750 0.8676 0.01896 0.01009 -0.0568 0.0059 1.0000
5.000 0.8855 0.02008 0.01141 -0.0549 0.0056 1.0000
5.250 0.9033 0.02122 0.01260 -0.0530 0.0054 1.0000
5.500 0.9212 0.02254 0.01399 -0.0511 0.0052 1.0000
5.750 0.9400 0.02385 0.01537 -0.0494 0.0052 1.0000
6.000 0.9594 0.02541 0.01702 -0.0477 0.0051 1.0000
6.250 0.9794 0.02699 0.01872 -0.0461 0.0051 1.0000
6.500 0.9992 0.02880 0.02071 -0.0445 0.0052 1.0000
6.750 1.0180 0.03071 0.02283 -0.0428 0.0053 1.0000
7.000 1.0353 0.03274 0.02512 -0.0410 0.0054 1.0000
7.250 1.0500 0.03517 0.02788 -0.0387 0.0055 1.0000
7.500 1.0628 0.03754 0.03060 -0.0364 0.0057 1.0000
7.750 1.0725 0.04017 0.03356 -0.0339 0.0059 1.0000
8.000 1.0796 0.04296 0.03667 -0.0312 0.0061 1.0000
8.250 1.0827 0.04609 0.04011 -0.0282 0.0063 1.0000
8.500 1.0837 0.04920 0.04349 -0.0253 0.0065 1.0000
8.750 1.0796 0.05276 0.04731 -0.0222 0.0067 1.0000
9.000 1.0732 0.05644 0.05120 -0.0193 0.0068 1.0000
9.250 1.0891 0.06365 0.05851 -0.0185 0.0128 1.0000
9.500 1.0773 0.06638 0.06148 -0.0151 0.0128 1.0000
9.750 1.0610 0.06906 0.06433 -0.0114 0.0128 1.0000
10.000 1.0428 0.07223 0.06767 -0.0090 0.0128 1.0000
10.250 1.0253 0.07564 0.07125 -0.0081 0.0128 1.0000
10.500 1.0083 0.07994 0.07570 -0.0087 0.0128 1.0000
10.750 0.9921 0.08472 0.08062 -0.0107 0.0128 1.0000
11.000 0.9764 0.09012 0.08616 -0.0140 0.0128 1.0000
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Polar data table (+)
Polar graphs
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