M6 (65%) (m665-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: M6 (65%) (m665-il) Reynolds number: 100,000 Max Cl/Cd: 47.33 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m665-il-100000.txt Download as CSV file: xf-m665-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: M6 (65%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5374 0.08943 0.08456 -0.0104 1.0000 0.0958
-8.000 -0.5471 0.08582 0.08101 -0.0134 1.0000 0.0983
-7.750 -0.5701 0.08286 0.07799 -0.0190 1.0000 0.1009
-7.500 -0.5674 0.07777 0.07293 -0.0191 1.0000 0.1028
-7.250 -0.5504 0.07465 0.06989 -0.0162 1.0000 0.1085
-7.000 -0.5641 0.07225 0.06718 -0.0201 1.0000 0.1152
-6.750 -0.5480 0.06730 0.06246 -0.0176 1.0000 0.1202
-6.500 -0.5563 0.06590 0.06058 -0.0192 1.0000 0.1300
-6.250 -0.5374 0.06051 0.05551 -0.0172 1.0000 0.1343
-6.000 -0.5349 0.05763 0.05237 -0.0170 1.0000 0.1458
-5.750 -0.5209 0.05428 0.04913 -0.0153 1.0000 0.1521
-5.500 -0.5132 0.05120 0.04594 -0.0141 1.0000 0.1636
-5.250 -0.5044 0.04845 0.04309 -0.0124 1.0000 0.1775
-5.000 -0.4943 0.04583 0.04042 -0.0105 1.0000 0.1927
-4.750 -0.4866 0.04378 0.03828 -0.0081 1.0000 0.2194
-4.500 -0.4582 0.03584 0.02886 -0.0070 1.0000 0.1136
-4.250 -0.4398 0.03043 0.02264 -0.0036 1.0000 0.0838
-4.000 -0.4224 0.02741 0.01918 -0.0011 1.0000 0.0790
-3.750 -0.4037 0.02528 0.01667 0.0011 1.0000 0.0791
-3.500 -0.3845 0.02374 0.01482 0.0031 1.0000 0.0824
-3.250 -0.3638 0.02208 0.01286 0.0049 1.0000 0.0834
-3.000 -0.3426 0.02074 0.01125 0.0067 1.0000 0.0855
-2.750 -0.3226 0.01949 0.00997 0.0081 1.0000 0.0910
-2.500 -0.3033 0.01862 0.00906 0.0097 1.0000 0.0972
-2.250 -0.2843 0.01773 0.00811 0.0114 1.0000 0.1030
-2.000 -0.0422 0.01249 0.00588 -0.0266 1.0000 1.0000
-1.750 -0.0273 0.01244 0.00570 -0.0245 1.0000 1.0000
-1.500 -0.0145 0.01245 0.00562 -0.0222 1.0000 1.0000
-1.250 -0.0061 0.01257 0.00566 -0.0191 1.0000 1.0000
-1.000 -0.0055 0.01284 0.00587 -0.0150 1.0000 1.0000
-0.750 -0.0094 0.01325 0.00622 -0.0105 1.0000 1.0000
-0.500 0.0098 0.01361 0.00649 -0.0104 0.9957 1.0000
-0.250 0.0696 0.01375 0.00650 -0.0175 0.9829 1.0000
0.000 0.1278 0.01379 0.00646 -0.0242 0.9701 1.0000
0.250 0.1851 0.01374 0.00636 -0.0305 0.9570 1.0000
0.500 0.2418 0.01360 0.00622 -0.0365 0.9434 1.0000
0.750 0.2942 0.01344 0.00606 -0.0414 0.9283 1.0000
1.000 0.3399 0.01330 0.00593 -0.0448 0.9108 1.0000
1.250 0.3757 0.01325 0.00590 -0.0462 0.8902 1.0000
1.500 0.4073 0.01323 0.00588 -0.0464 0.8704 1.0000
1.750 0.4321 0.01333 0.00598 -0.0454 0.8494 1.0000
2.000 0.4550 0.01345 0.00612 -0.0440 0.8291 1.0000
2.250 0.4771 0.01357 0.00622 -0.0422 0.8094 1.0000
2.500 0.4974 0.01375 0.00641 -0.0402 0.7878 1.0000
2.750 0.5186 0.01389 0.00654 -0.0382 0.7678 1.0000
3.000 0.5395 0.01408 0.00678 -0.0364 0.7471 1.0000
3.250 0.5608 0.01426 0.00700 -0.0346 0.7271 1.0000
3.500 0.5825 0.01443 0.00717 -0.0328 0.7077 1.0000
3.750 0.6028 0.01456 0.00735 -0.0307 0.6828 1.0000
4.000 0.6227 0.01459 0.00741 -0.0282 0.6542 1.0000
4.250 0.6413 0.01451 0.00726 -0.0254 0.6184 1.0000
4.500 0.6592 0.01444 0.00713 -0.0225 0.5750 1.0000
4.750 0.6774 0.01448 0.00715 -0.0199 0.5265 1.0000
5.000 0.6938 0.01466 0.00717 -0.0171 0.4546 1.0000
5.250 0.6961 0.01649 0.00761 -0.0125 0.2028 1.0000
5.500 0.7025 0.01904 0.00924 -0.0092 0.1041 1.0000
5.750 0.7172 0.02044 0.01055 -0.0068 0.0874 1.0000
6.000 0.7327 0.02199 0.01200 -0.0045 0.0797 1.0000
6.250 0.7529 0.02336 0.01340 -0.0028 0.0744 1.0000
6.500 0.7738 0.02515 0.01506 -0.0016 0.0695 1.0000
6.750 0.7964 0.02686 0.01694 -0.0003 0.0662 1.0000
7.000 0.8193 0.02865 0.01895 0.0010 0.0642 1.0000
7.250 0.8415 0.03078 0.02136 0.0023 0.0633 1.0000
7.500 0.8615 0.03322 0.02416 0.0040 0.0632 1.0000
7.750 0.8790 0.03602 0.02736 0.0058 0.0639 1.0000
8.000 0.8939 0.03921 0.03095 0.0078 0.0653 1.0000
8.250 0.9058 0.04266 0.03480 0.0099 0.0663 1.0000
8.500 0.9144 0.04604 0.03858 0.0122 0.0665 1.0000
8.750 0.9212 0.05007 0.04291 0.0142 0.0673 1.0000
9.000 0.9106 0.05519 0.04896 0.0183 0.0774 1.0000
|
Polar data table (+)
Polar graphs
<< Back to M6 (65%) (m665-il)