Coanda 3 (coanda3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Coanda 3 (coanda3-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.87 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-coanda3-il-1000000-n5.txt Download as CSV file: xf-coanda3-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 3
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4356 0.12567 0.12399 -0.0176 1.0000 0.0033
-11.500 -0.4329 0.12212 0.12045 -0.0184 1.0000 0.0033
-10.000 -0.4282 0.10058 0.09901 -0.0223 1.0000 0.0035
-9.000 -0.4210 0.08834 0.08684 -0.0259 0.9991 0.0037
-8.750 -0.4141 0.08188 0.08040 -0.0319 0.9970 0.0036
-8.500 -0.4036 0.07822 0.07674 -0.0364 0.9943 0.0037
-8.250 -0.3941 0.07397 0.07249 -0.0420 0.9899 0.0038
-8.000 -0.3770 0.06815 0.06666 -0.0498 0.9870 0.0039
-7.750 -0.3637 0.06289 0.06137 -0.0556 0.9815 0.0039
-7.000 -0.3100 0.03987 0.03795 -0.0743 0.9678 0.0030
-6.750 -0.2967 0.03083 0.02857 -0.0767 0.9598 0.0028
-6.500 -0.2761 0.02325 0.02039 -0.0783 0.9557 0.0027
-6.250 -0.2582 0.02005 0.01675 -0.0772 0.9489 0.0025
-6.000 -0.2356 0.01732 0.01358 -0.0766 0.9442 0.0024
-5.750 -0.2109 0.01520 0.01106 -0.0759 0.9403 0.0023
-5.500 -0.1880 0.01364 0.00922 -0.0747 0.9346 0.0023
-5.250 -0.1609 0.01215 0.00747 -0.0744 0.9291 0.0023
-5.000 -0.1359 0.01109 0.00622 -0.0735 0.9228 0.0025
-4.750 -0.1097 0.01016 0.00514 -0.0730 0.9163 0.0025
-4.500 -0.0842 0.00951 0.00437 -0.0723 0.9101 0.0030
-4.250 -0.0583 0.00898 0.00373 -0.0717 0.9035 0.0032
-4.000 -0.0325 0.00850 0.00314 -0.0712 0.8977 0.0035
-3.750 -0.0067 0.00823 0.00284 -0.0707 0.8907 0.0041
-3.500 0.0195 0.00800 0.00254 -0.0703 0.8828 0.0049
-3.250 0.0450 0.00771 0.00217 -0.0696 0.8748 0.0054
-3.000 0.0700 0.00741 0.00177 -0.0689 0.8663 0.0064
-2.750 0.0956 0.00726 0.00154 -0.0683 0.8563 0.0076
-2.500 0.1208 0.00716 0.00136 -0.0676 0.8413 0.0094
-2.250 0.1457 0.00707 0.00114 -0.0668 0.8230 0.0130
-2.000 0.1668 0.00687 0.00094 -0.0652 0.7891 0.0557
-1.750 0.1864 0.00701 0.00092 -0.0633 0.7379 0.0696
-1.500 0.2078 0.00714 0.00091 -0.0619 0.7034 0.0759
-1.250 0.2309 0.00723 0.00090 -0.0608 0.6759 0.0791
-1.000 0.2548 0.00731 0.00090 -0.0600 0.6518 0.0823
-0.750 0.2782 0.00743 0.00090 -0.0590 0.6227 0.0840
-0.500 0.3015 0.00749 0.00087 -0.0581 0.5948 0.0869
-0.250 0.3246 0.00760 0.00087 -0.0571 0.5613 0.0893
0.000 0.3474 0.00774 0.00089 -0.0560 0.5220 0.0924
0.250 0.3692 0.00798 0.00094 -0.0548 0.4699 0.0950
0.500 0.3908 0.00825 0.00101 -0.0536 0.4152 0.0967
0.750 0.4138 0.00845 0.00108 -0.0527 0.3778 0.0991
1.000 0.4376 0.00858 0.00115 -0.0520 0.3521 0.1041
1.250 0.4617 0.00871 0.00121 -0.0513 0.3316 0.1091
1.500 0.4865 0.00879 0.00128 -0.0507 0.3178 0.1145
1.750 0.5113 0.00885 0.00135 -0.0502 0.3069 0.1245
2.250 0.5559 0.00857 0.00157 -0.0482 0.2880 0.3517
2.500 0.5525 0.00728 0.00167 -0.0415 0.2746 0.8830
3.000 0.6874 0.00850 0.00250 -0.0609 0.1455 0.9843
3.250 0.7100 0.00971 0.00313 -0.0605 0.0155 0.9896
3.500 0.7501 0.01003 0.00348 -0.0634 0.0084 0.9948
3.750 0.7872 0.01030 0.00379 -0.0658 0.0064 0.9970
4.000 0.8218 0.01063 0.00414 -0.0676 0.0046 0.9989
4.250 0.8533 0.01094 0.00449 -0.0687 0.0038 1.0000
4.500 0.8733 0.01136 0.00495 -0.0672 0.0033 1.0000
4.750 0.8928 0.01183 0.00549 -0.0655 0.0030 1.0000
5.000 0.9122 0.01231 0.00604 -0.0638 0.0028 1.0000
5.250 0.9321 0.01272 0.00651 -0.0623 0.0024 1.0000
5.500 0.9507 0.01326 0.00712 -0.0606 0.0022 1.0000
5.750 0.9710 0.01360 0.00750 -0.0593 0.0020 1.0000
6.000 0.9877 0.01429 0.00825 -0.0572 0.0018 1.0000
6.250 1.0019 0.01517 0.00925 -0.0547 0.0017 1.0000
6.500 1.0189 0.01582 0.00999 -0.0526 0.0015 1.0000
6.750 1.0326 0.01678 0.01106 -0.0500 0.0014 1.0000
7.000 1.0431 0.01821 0.01262 -0.0466 0.0013 1.0000
7.250 1.0558 0.01967 0.01421 -0.0438 0.0011 1.0000
7.500 1.0688 0.02187 0.01657 -0.0409 0.0011 1.0000
7.750 1.0835 0.02382 0.01869 -0.0385 0.0010 1.0000
8.000 1.0966 0.02686 0.02200 -0.0356 0.0010 1.0000
8.250 1.1053 0.02989 0.02531 -0.0321 0.0010 1.0000
8.500 1.1115 0.03257 0.02826 -0.0285 0.0011 1.0000
8.750 1.1131 0.03558 0.03155 -0.0243 0.0012 1.0000
9.000 1.1133 0.03805 0.03428 -0.0203 0.0012 1.0000
9.250 1.1083 0.04075 0.03722 -0.0157 0.0012 1.0000
9.500 1.0980 0.04330 0.03998 -0.0105 0.0013 1.0000
9.750 1.0817 0.04575 0.04262 -0.0047 0.0013 1.0000
10.000 1.0707 0.04786 0.04488 -0.0007 0.0013 1.0000
10.250 1.0527 0.05097 0.04817 0.0031 0.0013 1.0000
10.500 1.0370 0.05403 0.05139 0.0055 0.0014 1.0000
10.750 1.0204 0.05759 0.05510 0.0069 0.0014 1.0000
11.000 1.0026 0.06179 0.05944 0.0069 0.0014 1.0000
11.250 0.9818 0.06722 0.06502 0.0052 0.0014 1.0000
11.500 0.9635 0.07306 0.07099 0.0022 0.0014 1.0000
11.750 0.9492 0.07929 0.07733 -0.0018 0.0014 1.0000
12.000 0.9308 0.08746 0.08562 -0.0075 0.0014 1.0000
12.250 0.9157 0.09606 0.09432 -0.0135 0.0014 1.0000
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Polar data table (+)
Polar graphs
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