Coanda 3 (coanda3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 3 (coanda3-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.02 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda3-il-1000000.txt Download as CSV file: xf-coanda3-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4606 0.08461 0.08313 -0.0232 1.0000 0.0072
-8.750 -0.4716 0.08198 0.08053 -0.0222 1.0000 0.0073
-8.500 -0.4931 0.07772 0.07632 -0.0224 0.9992 0.0070
-8.250 -0.4730 0.07487 0.07346 -0.0276 0.9971 0.0075
-8.000 -0.4532 0.06859 0.06714 -0.0363 0.9946 0.0076
-7.750 -0.4365 0.06307 0.06158 -0.0428 0.9911 0.0078
-7.500 -0.4168 0.05667 0.05510 -0.0499 0.9876 0.0080
-7.250 -0.3941 0.04920 0.04749 -0.0570 0.9848 0.0081
-7.000 -0.3704 0.04083 0.03891 -0.0632 0.9828 0.0085
-6.750 -0.3641 0.03024 0.02792 -0.0642 0.9755 0.0085
-6.500 -0.3446 0.02413 0.02131 -0.0649 0.9728 0.0087
-6.250 -0.3191 0.02137 0.01820 -0.0654 0.9714 0.0093
-6.000 -0.2910 0.01932 0.01582 -0.0659 0.9703 0.0099
-5.750 -0.2552 0.01993 0.01636 -0.0671 0.9698 0.0113
-5.000 -0.1880 0.01164 0.00681 -0.0633 0.9595 0.0076
-4.750 -0.1551 0.01069 0.00577 -0.0644 0.9580 0.0084
-4.500 -0.1218 0.00994 0.00494 -0.0654 0.9564 0.0092
-4.250 -0.0991 0.00946 0.00438 -0.0641 0.9508 0.0100
-4.000 -0.0687 0.00909 0.00396 -0.0645 0.9474 0.0108
-3.750 -0.0364 0.00870 0.00353 -0.0653 0.9445 0.0113
-3.500 -0.0089 0.00821 0.00296 -0.0650 0.9395 0.0113
-3.250 0.0177 0.00773 0.00240 -0.0645 0.9341 0.0120
-3.000 0.0493 0.00737 0.00189 -0.0652 0.9299 0.0143
-2.750 0.0743 0.00720 0.00166 -0.0643 0.9226 0.0162
-2.500 0.1046 0.00702 0.00142 -0.0647 0.9167 0.0202
-2.250 0.1283 0.00673 0.00134 -0.0638 0.9088 0.0709
-2.000 0.1572 0.00668 0.00128 -0.0639 0.9006 0.0775
-1.750 0.1839 0.00667 0.00127 -0.0636 0.8895 0.0832
-1.500 0.2104 0.00671 0.00130 -0.0631 0.8761 0.0863
-1.250 0.2354 0.00662 0.00117 -0.0624 0.8610 0.0905
-1.000 0.2598 0.00658 0.00112 -0.0615 0.8401 0.0944
-0.750 0.2846 0.00662 0.00109 -0.0608 0.8164 0.0983
-0.500 0.3078 0.00666 0.00102 -0.0596 0.7841 0.0995
-0.250 0.3298 0.00674 0.00096 -0.0582 0.7516 0.1012
0.000 0.3517 0.00679 0.00092 -0.0568 0.7228 0.1059
0.250 0.3745 0.00687 0.00092 -0.0557 0.6982 0.1097
0.500 0.3980 0.00695 0.00093 -0.0547 0.6746 0.1134
0.750 0.4212 0.00700 0.00094 -0.0537 0.6525 0.1211
1.000 0.4443 0.00707 0.00096 -0.0527 0.6281 0.1313
1.250 0.4665 0.00709 0.00100 -0.0515 0.5990 0.1641
1.500 0.4651 0.00574 0.00109 -0.0456 0.5726 0.7323
1.750 0.5589 0.00650 0.00177 -0.0612 0.4035 0.9828
2.000 0.6056 0.00706 0.00201 -0.0658 0.3371 0.9888
2.250 0.6423 0.00739 0.00220 -0.0680 0.3043 0.9930
2.500 0.6821 0.00770 0.00234 -0.0710 0.2667 0.9959
2.750 0.7175 0.00806 0.00245 -0.0731 0.2149 0.9982
3.000 0.7497 0.00864 0.00266 -0.0746 0.1442 1.0000
3.250 0.7592 0.00979 0.00321 -0.0712 0.0188 1.0000
3.500 0.7808 0.00999 0.00345 -0.0699 0.0150 1.0000
3.750 0.8020 0.01022 0.00375 -0.0685 0.0134 1.0000
4.000 0.8228 0.01052 0.00410 -0.0671 0.0122 1.0000
4.250 0.8408 0.01113 0.00483 -0.0650 0.0097 1.0000
4.750 0.8781 0.01221 0.00608 -0.0612 0.0085 1.0000
5.000 0.8972 0.01270 0.00662 -0.0595 0.0082 1.0000
5.250 0.9165 0.01316 0.00713 -0.0578 0.0076 1.0000
5.500 0.9341 0.01378 0.00781 -0.0558 0.0073 1.0000
5.750 0.9526 0.01430 0.00836 -0.0540 0.0064 1.0000
6.000 0.9684 0.01509 0.00922 -0.0517 0.0062 1.0000
6.250 0.9839 0.01594 0.01012 -0.0494 0.0058 1.0000
6.500 0.9978 0.01709 0.01137 -0.0467 0.0058 1.0000
7.750 1.0170 0.02051 0.01609 -0.0270 0.0088 1.0000
8.000 1.0360 0.01846 0.01408 -0.0251 0.0080 1.0000
8.250 1.0487 0.01928 0.01501 -0.0228 0.0073 1.0000
8.500 1.0570 0.02088 0.01677 -0.0199 0.0069 1.0000
8.750 1.0633 0.02240 0.01842 -0.0169 0.0064 1.0000
9.000 1.0657 0.02440 0.02057 -0.0134 0.0062 1.0000
9.250 1.0667 0.02614 0.02242 -0.0101 0.0059 1.0000
9.500 1.0624 0.02828 0.02471 -0.0058 0.0058 1.0000
9.750 1.0601 0.02998 0.02647 -0.0022 0.0056 1.0000
10.000 1.0509 0.03220 0.02880 0.0021 0.0055 1.0000
10.250 1.0373 0.03616 0.03285 0.0057 0.0052 1.0000
10.500 1.0234 0.03788 0.03472 0.0096 0.0052 1.0000
10.750 0.9668 0.04752 0.04464 0.0140 0.0049 1.0000
11.000 0.9372 0.05251 0.04980 0.0159 0.0049 1.0000
11.250 0.9263 0.05511 0.05249 0.0165 0.0049 1.0000
11.500 0.9205 0.05727 0.05473 0.0166 0.0050 1.0000
11.750 0.9232 0.05756 0.05511 0.0163 0.0053 1.0000
12.000 0.8963 0.06460 0.06225 0.0149 0.0052 1.0000
12.250 0.8770 0.07035 0.06812 0.0129 0.0052 1.0000
12.500 0.8568 0.07676 0.07465 0.0099 0.0053 1.0000
12.750 0.8177 0.08822 0.08635 0.0029 0.0057 1.0000
13.000 0.7998 0.09538 0.09358 -0.0006 0.0056 1.0000
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Polar data table (+)
Polar graphs
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