Coanda 2 (coanda2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 2 (coanda2-il) Reynolds number: 1,000,000 Max Cl/Cd: 58.9 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda2-il-1000000-n5.txt Download as CSV file: xf-coanda2-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4529 0.08612 0.08463 -0.0152 1.0000 0.0026
-8.500 -0.4610 0.08292 0.08146 -0.0151 1.0000 0.0024
-8.250 -0.4694 0.08087 0.07944 -0.0137 1.0000 0.0026
-8.000 -0.4726 0.07635 0.07495 -0.0158 0.9995 0.0026
-7.750 -0.4539 0.06971 0.06829 -0.0244 0.9970 0.0027
-7.500 -0.4350 0.06065 0.05918 -0.0353 0.9933 0.0025
-7.250 -0.4178 0.04481 0.04308 -0.0501 0.9878 0.0023
-7.000 -0.4121 0.02839 0.02589 -0.0566 0.9798 0.0021
-6.750 -0.4033 0.01948 0.01623 -0.0554 0.9739 0.0021
-6.500 -0.3815 0.01690 0.01328 -0.0546 0.9698 0.0021
-6.250 -0.3559 0.01483 0.01085 -0.0543 0.9673 0.0021
-6.000 -0.3359 0.01363 0.00945 -0.0526 0.9607 0.0022
-5.750 -0.3088 0.01258 0.00820 -0.0524 0.9567 0.0024
-5.500 -0.2788 0.01157 0.00697 -0.0528 0.9533 0.0025
-5.250 -0.2520 0.01084 0.00607 -0.0523 0.9465 0.0027
-5.000 -0.2160 0.01023 0.00533 -0.0540 0.9417 0.0031
-4.750 -0.1837 0.00964 0.00460 -0.0549 0.9347 0.0034
-4.500 -0.1500 0.00908 0.00396 -0.0562 0.9284 0.0041
-4.250 -0.1180 0.00866 0.00345 -0.0570 0.9199 0.0048
-4.000 -0.0857 0.00830 0.00298 -0.0578 0.9095 0.0055
-3.750 -0.0562 0.00789 0.00241 -0.0580 0.8980 0.0067
-3.250 -0.0019 0.00748 0.00179 -0.0574 0.8719 0.0121
-3.000 0.0224 0.00709 0.00153 -0.0566 0.8577 0.0548
-2.750 0.0499 0.00732 0.00179 -0.0563 0.8403 0.0639
-2.500 0.0758 0.00755 0.00193 -0.0556 0.8157 0.0673
-2.250 0.0992 0.00771 0.00194 -0.0544 0.7785 0.0683
-2.000 0.1201 0.00813 0.00215 -0.0527 0.7191 0.0692
-1.750 0.1394 0.00835 0.00210 -0.0507 0.6553 0.0694
-1.500 0.1613 0.00848 0.00205 -0.0493 0.6136 0.0695
-1.250 0.1841 0.00842 0.00186 -0.0482 0.5822 0.0702
-1.000 0.2071 0.00834 0.00166 -0.0471 0.5526 0.0710
-0.750 0.2300 0.00838 0.00155 -0.0460 0.5139 0.0717
-0.500 0.2530 0.00845 0.00148 -0.0450 0.4749 0.0722
-0.250 0.2765 0.00854 0.00143 -0.0441 0.4429 0.0727
0.000 0.3008 0.00858 0.00140 -0.0433 0.4188 0.0731
0.250 0.3253 0.00864 0.00137 -0.0426 0.3991 0.0734
0.500 0.3501 0.00867 0.00135 -0.0419 0.3809 0.0737
0.750 0.3753 0.00869 0.00134 -0.0413 0.3693 0.0741
1.000 0.4006 0.00870 0.00134 -0.0408 0.3576 0.0744
1.250 0.4261 0.00872 0.00134 -0.0403 0.3468 0.0748
1.500 0.4513 0.00876 0.00136 -0.0397 0.3339 0.0751
1.750 0.4727 0.00910 0.00144 -0.0385 0.2709 0.0755
2.000 0.4958 0.00933 0.00153 -0.0376 0.2308 0.0760
2.250 0.5180 0.00966 0.00167 -0.0366 0.1837 0.0767
2.500 0.5372 0.01027 0.00191 -0.0350 0.1026 0.0775
2.750 0.5566 0.01093 0.00228 -0.0334 0.0146 0.0780
3.000 0.5814 0.01106 0.00246 -0.0328 0.0104 0.0786
3.250 0.6061 0.01119 0.00265 -0.0322 0.0081 0.0797
3.500 0.6307 0.01135 0.00286 -0.0315 0.0068 0.0808
3.750 0.6542 0.01162 0.00324 -0.0306 0.0055 0.0819
4.000 0.6785 0.01181 0.00347 -0.0300 0.0047 0.0830
4.250 0.7023 0.01204 0.00375 -0.0292 0.0041 0.0843
4.500 0.7256 0.01232 0.00407 -0.0283 0.0035 0.0871
4.750 0.7468 0.01283 0.00470 -0.0270 0.0032 0.0905
5.000 0.7681 0.01334 0.00532 -0.0257 0.0029 0.0934
5.250 0.7880 0.01395 0.00602 -0.0241 0.0028 0.0956
5.500 0.8055 0.01476 0.00694 -0.0221 0.0026 0.0990
5.750 0.8232 0.01553 0.00780 -0.0201 0.0025 0.1059
6.000 0.8401 0.01474 0.00852 -0.0185 0.0022 0.8133
6.500 1.0329 0.02069 0.01521 -0.0511 0.0013 0.9973
6.750 1.0643 0.02297 0.01771 -0.0520 0.0012 0.9991
7.000 1.0898 0.02537 0.02036 -0.0518 0.0012 1.0000
7.250 1.1048 0.02761 0.02283 -0.0494 0.0012 1.0000
7.500 1.1179 0.02990 0.02537 -0.0468 0.0013 1.0000
7.750 1.1279 0.03261 0.02835 -0.0438 0.0013 1.0000
8.000 1.1352 0.03548 0.03148 -0.0406 0.0014 1.0000
8.250 1.1409 0.03812 0.03436 -0.0375 0.0014 1.0000
8.500 1.1422 0.04109 0.03759 -0.0340 0.0014 1.0000
8.750 1.1415 0.04389 0.04061 -0.0305 0.0015 1.0000
9.000 1.1348 0.04710 0.04404 -0.0267 0.0015 1.0000
9.250 1.1284 0.04981 0.04693 -0.0231 0.0015 1.0000
9.500 1.1071 0.05232 0.04959 -0.0175 0.0016 1.0000
9.750 1.0900 0.05492 0.05235 -0.0138 0.0016 1.0000
10.000 1.0721 0.05823 0.05579 -0.0119 0.0016 1.0000
10.250 1.0544 0.06222 0.05992 -0.0118 0.0016 1.0000
10.500 1.0388 0.06687 0.06470 -0.0135 0.0016 1.0000
10.750 1.0208 0.07312 0.07108 -0.0174 0.0016 1.0000
11.000 1.0034 0.08059 0.07869 -0.0228 0.0016 1.0000
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Polar data table (+)
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