Coanda 1 (coanda1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 1 (coanda1-il) Reynolds number: 1,000,000 Max Cl/Cd: 57.68 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda1-il-1000000-n5.txt Download as CSV file: xf-coanda1-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4441 0.10440 0.10279 -0.0106 1.0000 0.0016
-9.000 -0.4396 0.09825 0.09668 -0.0121 1.0000 0.0024
-8.750 -0.4427 0.09332 0.09177 -0.0130 1.0000 0.0018
-8.500 -0.4394 0.09167 0.09014 -0.0134 1.0000 0.0023
-8.250 -0.4460 0.08727 0.08577 -0.0139 1.0000 0.0017
-8.000 -0.4456 0.08577 0.08429 -0.0138 1.0000 0.0025
-7.750 -0.4587 0.08296 0.08153 -0.0125 1.0000 0.0022
-7.500 -0.4644 0.07938 0.07797 -0.0125 1.0000 0.0021
-7.250 -0.4457 0.07345 0.07202 -0.0199 0.9979 0.0021
-6.750 -0.4019 0.06381 0.06229 -0.0321 0.9926 0.0027
-6.500 -0.3767 0.05719 0.05561 -0.0393 0.9890 0.0029
-6.250 -0.3530 0.05075 0.04906 -0.0450 0.9848 0.0028
-6.000 -0.3313 0.04259 0.04072 -0.0498 0.9798 0.0026
-5.750 -0.3177 0.03279 0.03056 -0.0515 0.9729 0.0025
-5.500 -0.3100 0.01955 0.01638 -0.0500 0.9674 0.0022
-5.250 -0.2970 0.01584 0.01211 -0.0469 0.9598 0.0021
-5.000 -0.2719 0.01374 0.00961 -0.0463 0.9566 0.0022
-4.750 -0.2447 0.01230 0.00789 -0.0460 0.9534 0.0022
-4.500 -0.2191 0.01131 0.00671 -0.0454 0.9481 0.0023
-4.250 -0.1882 0.01039 0.00559 -0.0459 0.9444 0.0024
-4.000 -0.1546 0.00971 0.00478 -0.0471 0.9411 0.0028
-3.750 -0.1250 0.00922 0.00417 -0.0473 0.9346 0.0033
-3.500 -0.0917 0.00873 0.00356 -0.0484 0.9290 0.0034
-3.250 -0.0597 0.00827 0.00305 -0.0493 0.9198 0.0046
-3.000 -0.0269 0.00791 0.00258 -0.0503 0.9063 0.0054
-2.750 0.0037 0.00759 0.00208 -0.0507 0.8851 0.0067
-2.500 0.0298 0.00739 0.00171 -0.0502 0.8559 0.0096
-2.250 0.0536 0.00732 0.00147 -0.0491 0.8184 0.0160
-2.000 0.0726 0.00725 0.00134 -0.0471 0.7609 0.0585
-1.750 0.0946 0.00752 0.00146 -0.0456 0.7151 0.0634
-1.500 0.1181 0.00778 0.00159 -0.0445 0.6771 0.0666
-1.250 0.1419 0.00802 0.00169 -0.0436 0.6392 0.0689
-1.000 0.1654 0.00816 0.00166 -0.0426 0.6026 0.0702
-0.750 0.1891 0.00818 0.00156 -0.0417 0.5719 0.0707
-0.500 0.2131 0.00826 0.00152 -0.0408 0.5410 0.0714
-0.250 0.2376 0.00830 0.00145 -0.0401 0.5179 0.0718
0.000 0.2627 0.00835 0.00144 -0.0395 0.4992 0.0722
0.250 0.2879 0.00839 0.00143 -0.0390 0.4808 0.0725
0.500 0.3126 0.00844 0.00140 -0.0383 0.4588 0.0727
0.750 0.3367 0.00844 0.00131 -0.0376 0.4308 0.0738
1.000 0.3601 0.00853 0.00126 -0.0367 0.3909 0.0747
1.250 0.3830 0.00872 0.00129 -0.0358 0.3449 0.0756
1.500 0.4068 0.00887 0.00134 -0.0350 0.3136 0.0763
1.750 0.4312 0.00898 0.00138 -0.0343 0.2909 0.0769
2.000 0.4547 0.00917 0.00145 -0.0335 0.2553 0.0775
2.250 0.4766 0.00950 0.00156 -0.0325 0.1985 0.0780
2.500 0.4998 0.00974 0.00168 -0.0316 0.1656 0.0786
2.750 0.5234 0.00994 0.00179 -0.0309 0.1406 0.0792
3.000 0.5449 0.01033 0.00195 -0.0298 0.0896 0.0797
3.250 0.5644 0.01094 0.00234 -0.0282 0.0134 0.0801
3.500 0.5889 0.01108 0.00253 -0.0276 0.0088 0.0808
3.750 0.6134 0.01122 0.00273 -0.0269 0.0070 0.0814
4.000 0.6368 0.01147 0.00308 -0.0260 0.0056 0.0823
4.250 0.6609 0.01165 0.00333 -0.0253 0.0047 0.0841
4.500 0.6847 0.01187 0.00358 -0.0246 0.0038 0.0853
4.750 0.7064 0.01231 0.00412 -0.0234 0.0034 0.0861
5.000 0.7283 0.01273 0.00462 -0.0222 0.0030 0.0880
5.250 0.7489 0.01329 0.00529 -0.0207 0.0028 0.0916
5.500 0.7676 0.01402 0.00613 -0.0189 0.0026 0.0942
5.750 0.7894 0.01439 0.00658 -0.0179 0.0023 0.0974
6.000 0.8119 0.01468 0.00691 -0.0171 0.0020 0.1001
6.250 0.8263 0.01577 0.00812 -0.0146 0.0019 0.1066
6.500 0.8437 0.01665 0.00911 -0.0124 0.0014 0.1237
7.000 0.9329 0.01982 0.01434 -0.0210 0.0012 0.9807
7.250 0.9596 0.02178 0.01650 -0.0210 0.0012 0.9840
7.500 0.9765 0.02381 0.01875 -0.0187 0.0012 0.9867
7.750 1.0026 0.02665 0.02189 -0.0188 0.0013 0.9884
8.000 1.0227 0.02967 0.02523 -0.0179 0.0014 0.9898
8.250 1.0396 0.03215 0.02796 -0.0168 0.0015 0.9912
8.500 1.0516 0.03517 0.03126 -0.0151 0.0016 0.9931
8.750 1.0594 0.03820 0.03455 -0.0132 0.0017 0.9951
11.250 0.9378 0.07754 0.07552 -0.0039 0.0019 1.0000
11.500 0.9222 0.08437 0.08244 -0.0084 0.0019 1.0000
11.750 0.9073 0.09208 0.09025 -0.0137 0.0019 1.0000
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Polar data table (+)
Polar graphs
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