GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.35 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe11k-il-1000000.txt Download as CSV file: xf-goe11k-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 11K AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5064 0.11366 0.11201 -0.0214 1.0000 0.0130
-10.250 -0.7527 0.03337 0.03100 -0.0787 0.9853 0.0088
-10.000 -0.7642 0.02575 0.02267 -0.0773 0.9787 0.0090
-9.750 -0.7460 0.02316 0.01977 -0.0775 0.9766 0.0094
-9.500 -0.7203 0.02191 0.01837 -0.0782 0.9754 0.0097
-9.250 -0.6948 0.02050 0.01677 -0.0788 0.9745 0.0100
-9.000 -0.6681 0.01925 0.01533 -0.0795 0.9737 0.0104
-8.750 -0.6521 0.01832 0.01425 -0.0775 0.9696 0.0107
-8.500 -0.6297 0.01728 0.01302 -0.0769 0.9669 0.0112
-8.250 -0.6036 0.01641 0.01200 -0.0770 0.9653 0.0115
-8.000 -0.5753 0.01578 0.01123 -0.0774 0.9642 0.0118
-7.750 -0.5513 0.01408 0.00926 -0.0773 0.9630 0.0128
-7.500 -0.5217 0.01351 0.00862 -0.0780 0.9623 0.0136
-7.250 -0.4913 0.01302 0.00807 -0.0788 0.9617 0.0144
-7.000 -0.4604 0.01259 0.00756 -0.0797 0.9612 0.0153
-6.750 -0.4460 0.01226 0.00715 -0.0768 0.9556 0.0158
-6.500 -0.4211 0.01142 0.00619 -0.0763 0.9536 0.0172
-6.250 -0.3922 0.01099 0.00572 -0.0767 0.9524 0.0187
-6.000 -0.3622 0.01065 0.00534 -0.0773 0.9514 0.0203
-5.750 -0.3321 0.01023 0.00485 -0.0779 0.9506 0.0221
-5.500 -0.3013 0.00987 0.00451 -0.0787 0.9500 0.0253
-5.250 -0.2696 0.00966 0.00427 -0.0796 0.9494 0.0275
-5.000 -0.2380 0.00938 0.00405 -0.0805 0.9489 0.0326
-4.750 -0.2046 0.00932 0.00398 -0.0818 0.9485 0.0354
-4.500 -0.1888 0.00913 0.00380 -0.0791 0.9431 0.0389
-4.250 -0.1590 0.00909 0.00379 -0.0796 0.9414 0.0420
-4.000 -0.1278 0.00903 0.00372 -0.0804 0.9401 0.0445
-3.750 -0.0948 0.00904 0.00373 -0.0815 0.9392 0.0458
-3.500 -0.0649 0.00846 0.00311 -0.0822 0.9381 0.0497
-3.250 -0.0320 0.00826 0.00292 -0.0834 0.9373 0.0522
-3.000 0.0020 0.00808 0.00273 -0.0849 0.9364 0.0546
-2.750 0.0386 0.00788 0.00253 -0.0869 0.9354 0.0566
-2.500 0.0592 0.00776 0.00240 -0.0852 0.9304 0.0578
-2.250 0.0906 0.00759 0.00221 -0.0860 0.9276 0.0589
-2.000 0.1235 0.00728 0.00187 -0.0872 0.9255 0.0622
-1.750 0.1591 0.00708 0.00169 -0.0890 0.9237 0.0656
-1.500 0.1962 0.00692 0.00153 -0.0912 0.9220 0.0681
-1.250 0.2192 0.00682 0.00142 -0.0900 0.9153 0.0701
-1.000 0.2536 0.00669 0.00128 -0.0915 0.9104 0.0722
-0.750 0.2879 0.00651 0.00118 -0.0930 0.9068 0.0919
-0.500 0.3065 0.00620 0.00117 -0.0910 0.9010 0.1906
-0.250 0.3314 0.00559 0.00113 -0.0907 0.8953 0.3994
0.000 0.3457 0.00501 0.00115 -0.0878 0.8874 0.6062
0.250 0.3577 0.00433 0.00119 -0.0841 0.8806 0.8419
0.500 0.4817 0.00439 0.00154 -0.1062 0.8732 0.9629
0.750 0.5149 0.00454 0.00162 -0.1071 0.8548 0.9768
1.000 0.5560 0.00472 0.00172 -0.1100 0.8311 0.9861
1.250 0.5983 0.00489 0.00176 -0.1132 0.7972 0.9920
1.500 0.6327 0.00518 0.00178 -0.1146 0.7326 0.9968
1.750 0.6335 0.00634 0.00199 -0.1088 0.5138 1.0000
2.000 0.6393 0.00702 0.00221 -0.1041 0.4075 1.0000
2.250 0.6513 0.00751 0.00236 -0.1008 0.3275 1.0000
2.500 0.6593 0.00823 0.00258 -0.0968 0.2099 1.0000
2.750 0.6685 0.00899 0.00286 -0.0929 0.1000 1.0000
3.000 0.6868 0.00929 0.00305 -0.0909 0.0776 1.0000
3.250 0.7074 0.00946 0.00320 -0.0893 0.0720 1.0000
3.500 0.7279 0.00965 0.00336 -0.0878 0.0675 1.0000
3.750 0.7478 0.00987 0.00357 -0.0861 0.0627 1.0000
4.000 0.7685 0.01006 0.00377 -0.0845 0.0598 1.0000
4.250 0.7897 0.01020 0.00393 -0.0831 0.0577 1.0000
4.500 0.8105 0.01038 0.00411 -0.0816 0.0546 1.0000
4.750 0.8304 0.01063 0.00434 -0.0800 0.0503 1.0000
5.000 0.8510 0.01083 0.00456 -0.0784 0.0471 1.0000
5.250 0.8728 0.01094 0.00467 -0.0772 0.0435 1.0000
5.500 0.8925 0.01121 0.00489 -0.0755 0.0370 1.0000
5.750 0.9134 0.01139 0.00505 -0.0741 0.0324 1.0000
6.000 0.9327 0.01170 0.00533 -0.0724 0.0272 1.0000
6.250 0.9521 0.01202 0.00563 -0.0706 0.0237 1.0000
6.500 0.9704 0.01245 0.00609 -0.0687 0.0208 1.0000
6.750 0.9900 0.01275 0.00642 -0.0670 0.0194 1.0000
7.000 1.0086 0.01311 0.00679 -0.0651 0.0178 1.0000
7.250 1.0234 0.01384 0.00758 -0.0625 0.0158 1.0000
7.500 1.0420 0.01414 0.00793 -0.0606 0.0153 1.0000
7.750 1.0602 0.01448 0.00830 -0.0587 0.0145 1.0000
8.000 1.0781 0.01485 0.00871 -0.0568 0.0137 1.0000
8.250 1.0957 0.01528 0.00917 -0.0548 0.0129 1.0000
8.500 1.1106 0.01606 0.01001 -0.0524 0.0120 1.0000
8.750 1.1239 0.01713 0.01121 -0.0497 0.0115 1.0000
9.000 1.1422 0.01751 0.01165 -0.0479 0.0112 1.0000
9.250 1.1592 0.01808 0.01229 -0.0460 0.0109 1.0000
9.500 1.1761 0.01867 0.01296 -0.0440 0.0104 1.0000
9.750 1.1936 0.01911 0.01345 -0.0422 0.0099 1.0000
10.000 1.2105 0.01962 0.01401 -0.0404 0.0095 1.0000
10.250 1.2265 0.02022 0.01467 -0.0384 0.0091 1.0000
10.500 1.2396 0.02118 0.01572 -0.0360 0.0088 1.0000
10.750 1.2468 0.02302 0.01775 -0.0328 0.0084 1.0000
11.000 1.2576 0.02430 0.01921 -0.0301 0.0082 1.0000
11.250 1.2696 0.02525 0.02028 -0.0277 0.0081 1.0000
11.500 1.2815 0.02610 0.02126 -0.0253 0.0078 1.0000
11.750 1.2917 0.02712 0.02240 -0.0227 0.0077 1.0000
12.000 1.2964 0.02872 0.02419 -0.0194 0.0075 1.0000
12.250 1.3059 0.02961 0.02520 -0.0169 0.0073 1.0000
12.500 1.3094 0.03112 0.02687 -0.0137 0.0071 1.0000
12.750 1.3094 0.03294 0.02887 -0.0103 0.0070 1.0000
13.000 1.3160 0.03398 0.03001 -0.0079 0.0068 1.0000
13.250 1.3087 0.03644 0.03269 -0.0041 0.0068 1.0000
13.500 1.3138 0.03761 0.03393 -0.0020 0.0066 1.0000
13.750 1.3013 0.04062 0.03718 0.0015 0.0066 1.0000
14.000 1.3031 0.04222 0.03887 0.0034 0.0065 1.0000
14.250 1.2949 0.04491 0.04171 0.0057 0.0064 1.0000
14.500 1.2759 0.04901 0.04604 0.0077 0.0064 1.0000
14.750 1.2755 0.05118 0.04825 0.0085 0.0063 1.0000
15.000 1.2536 0.05630 0.05359 0.0088 0.0063 1.0000
15.250 1.2526 0.05904 0.05636 0.0085 0.0062 1.0000
15.500 1.1748 0.07600 0.07386 0.0003 0.0065 1.0000
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