SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD6080 (9.2%) (sd6080-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.66 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6080-il-1000000-n5.txt Download as CSV file: xf-sd6080-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD6080 (9.2%)
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 -0.3137 0.08256 0.08077 -0.0447 0.9153 0.0049
-8.500 -0.3100 0.07966 0.07779 -0.0459 0.8905 0.0051
-7.000 -0.3702 0.02004 0.01625 -0.0786 0.7944 0.0046
-6.750 -0.3482 0.01749 0.01326 -0.0786 0.7859 0.0046
-6.500 -0.3239 0.01590 0.01137 -0.0785 0.7780 0.0046
-6.250 -0.2985 0.01473 0.00995 -0.0784 0.7696 0.0047
-6.000 -0.2725 0.01373 0.00874 -0.0783 0.7618 0.0047
-5.750 -0.2460 0.01297 0.00781 -0.0782 0.7538 0.0049
-5.500 -0.2192 0.01226 0.00694 -0.0781 0.7460 0.0050
-5.000 -0.1651 0.01110 0.00551 -0.0779 0.7306 0.0054
-4.750 -0.1378 0.01063 0.00492 -0.0778 0.7231 0.0056
-4.500 -0.1102 0.01023 0.00443 -0.0777 0.7156 0.0060
-4.250 -0.0826 0.00989 0.00398 -0.0776 0.7080 0.0062
-4.000 -0.0548 0.00958 0.00361 -0.0776 0.7005 0.0064
-3.750 -0.0271 0.00932 0.00326 -0.0776 0.6931 0.0065
-3.500 0.0007 0.00889 0.00275 -0.0775 0.6857 0.0068
-3.250 0.0285 0.00862 0.00241 -0.0775 0.6786 0.0073
-3.000 0.0566 0.00842 0.00218 -0.0775 0.6715 0.0079
-2.750 0.0846 0.00826 0.00196 -0.0775 0.6644 0.0085
-2.500 0.1128 0.00810 0.00174 -0.0775 0.6575 0.0091
-2.000 0.1692 0.00783 0.00138 -0.0775 0.6437 0.0116
-1.750 0.1973 0.00771 0.00124 -0.0775 0.6366 0.0165
-1.500 0.2254 0.00751 0.00114 -0.0775 0.6300 0.0436
-1.250 0.2534 0.00736 0.00106 -0.0776 0.6228 0.0743
-1.000 0.2815 0.00722 0.00100 -0.0777 0.6161 0.1060
-0.750 0.3094 0.00708 0.00095 -0.0777 0.6086 0.1487
-0.500 0.3374 0.00692 0.00092 -0.0778 0.6012 0.2045
-0.250 0.3651 0.00673 0.00090 -0.0779 0.5927 0.2784
0.000 0.3930 0.00659 0.00090 -0.0780 0.5843 0.3398
0.250 0.4204 0.00640 0.00091 -0.0780 0.5755 0.4293
0.500 0.4481 0.00624 0.00093 -0.0781 0.5662 0.5069
0.750 0.4755 0.00609 0.00096 -0.0781 0.5572 0.5889
1.000 0.5022 0.00591 0.00101 -0.0779 0.5473 0.6853
1.250 0.5277 0.00568 0.00107 -0.0774 0.5369 0.7966
1.500 0.5493 0.00544 0.00113 -0.0757 0.5264 0.9196
1.750 0.5878 0.00546 0.00114 -0.0780 0.5130 1.0000
2.000 0.6153 0.00558 0.00119 -0.0779 0.4999 1.0000
2.250 0.6428 0.00570 0.00124 -0.0779 0.4866 1.0000
2.500 0.6702 0.00583 0.00132 -0.0778 0.4726 1.0000
2.750 0.6975 0.00598 0.00139 -0.0777 0.4572 1.0000
3.000 0.7247 0.00614 0.00148 -0.0776 0.4404 1.0000
3.250 0.7518 0.00631 0.00159 -0.0775 0.4225 1.0000
3.750 0.8053 0.00673 0.00183 -0.0773 0.3831 1.0000
4.000 0.8317 0.00698 0.00198 -0.0772 0.3607 1.0000
4.250 0.8580 0.00724 0.00215 -0.0770 0.3373 1.0000
4.500 0.8840 0.00753 0.00234 -0.0768 0.3132 1.0000
4.750 0.9092 0.00791 0.00257 -0.0765 0.2797 1.0000
5.000 0.9340 0.00833 0.00283 -0.0762 0.2470 1.0000
5.250 0.9589 0.00873 0.00309 -0.0758 0.2180 1.0000
5.500 0.9833 0.00918 0.00339 -0.0755 0.1863 1.0000
5.750 1.0074 0.00965 0.00370 -0.0750 0.1559 1.0000
6.000 1.0315 0.01010 0.00403 -0.0746 0.1308 1.0000
6.250 1.0554 0.01057 0.00437 -0.0742 0.1079 1.0000
6.500 1.0793 0.01101 0.00471 -0.0737 0.0879 1.0000
6.750 1.1028 0.01148 0.00509 -0.0732 0.0700 1.0000
7.000 1.1252 0.01205 0.00554 -0.0726 0.0490 1.0000
7.250 1.1477 0.01259 0.00600 -0.0719 0.0332 1.0000
7.500 1.1679 0.01335 0.00662 -0.0709 0.0130 1.0000
7.750 1.1908 0.01381 0.00707 -0.0703 0.0095 1.0000
8.000 1.2139 0.01421 0.00751 -0.0697 0.0085 1.0000
8.250 1.2365 0.01466 0.00798 -0.0691 0.0077 1.0000
8.500 1.2584 0.01514 0.00849 -0.0683 0.0070 1.0000
8.750 1.2805 0.01557 0.00897 -0.0676 0.0068 1.0000
9.000 1.3020 0.01603 0.00948 -0.0668 0.0066 1.0000
9.250 1.3228 0.01653 0.01003 -0.0659 0.0064 1.0000
9.500 1.3428 0.01707 0.01062 -0.0649 0.0062 1.0000
9.750 1.3619 0.01763 0.01123 -0.0638 0.0059 1.0000
10.000 1.3800 0.01822 0.01188 -0.0625 0.0058 1.0000
10.250 1.3967 0.01887 0.01259 -0.0611 0.0056 1.0000
10.500 1.4108 0.01953 0.01331 -0.0592 0.0055 1.0000
10.750 1.4219 0.02026 0.01411 -0.0569 0.0053 1.0000
11.000 1.4317 0.02107 0.01499 -0.0545 0.0052 1.0000
11.250 1.4396 0.02207 0.01606 -0.0521 0.0050 1.0000
11.500 1.4463 0.02321 0.01728 -0.0498 0.0049 1.0000
11.750 1.4492 0.02468 0.01886 -0.0473 0.0047 1.0000
12.000 1.4559 0.02597 0.02024 -0.0455 0.0047 1.0000
12.250 1.4646 0.02717 0.02151 -0.0440 0.0046 1.0000
12.500 1.4739 0.02838 0.02281 -0.0427 0.0045 1.0000
12.750 1.4801 0.02990 0.02442 -0.0413 0.0045 1.0000
13.000 1.4857 0.03155 0.02616 -0.0401 0.0044 1.0000
13.250 1.4903 0.03337 0.02807 -0.0390 0.0043 1.0000
13.500 1.4953 0.03522 0.03001 -0.0381 0.0043 1.0000
13.750 1.4961 0.03757 0.03247 -0.0373 0.0042 1.0000
14.000 1.4974 0.03997 0.03497 -0.0366 0.0041 1.0000
14.250 1.4990 0.04242 0.03753 -0.0362 0.0041 1.0000
14.500 1.4989 0.04517 0.04039 -0.0360 0.0040 1.0000
14.750 1.4951 0.04846 0.04379 -0.0359 0.0040 1.0000
15.000 1.4949 0.05143 0.04686 -0.0361 0.0039 1.0000
15.250 1.4926 0.05481 0.05036 -0.0365 0.0039 1.0000
15.500 1.4875 0.05870 0.05437 -0.0372 0.0038 1.0000
15.750 1.4816 0.06286 0.05866 -0.0381 0.0038 1.0000
16.000 1.4768 0.06706 0.06297 -0.0393 0.0037 1.0000
16.250 1.4676 0.07209 0.06813 -0.0409 0.0037 1.0000
16.500 1.4623 0.07670 0.07285 -0.0426 0.0037 1.0000
16.750 1.4530 0.08211 0.07839 -0.0447 0.0037 1.0000
17.000 1.4438 0.08772 0.08412 -0.0471 0.0036 1.0000
17.250 1.4328 0.09379 0.09031 -0.0497 0.0036 1.0000
17.500 1.4222 0.09998 0.09662 -0.0526 0.0036 1.0000
17.750 1.4123 0.10621 0.10297 -0.0557 0.0035 1.0000
18.000 1.3986 0.11329 0.11018 -0.0593 0.0035 1.0000
18.250 1.3863 0.12026 0.11727 -0.0629 0.0035 1.0000
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Polar data table (+)
Polar graphs
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