GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 500,000 Max Cl/Cd: 99.41 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe11k-il-500000-n5.txt Download as CSV file: xf-goe11k-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4656 0.09544 0.09314 -0.0406 0.9946 0.0060
-9.500 -0.4575 0.09221 0.08992 -0.0432 0.9930 0.0065
-9.000 -0.6053 0.03087 0.02760 -0.0850 0.9682 0.0055
-8.750 -0.5969 0.02638 0.02255 -0.0844 0.9644 0.0056
-8.500 -0.5857 0.02368 0.01945 -0.0828 0.9595 0.0058
-8.250 -0.5639 0.02209 0.01766 -0.0828 0.9573 0.0061
-8.000 -0.5397 0.02071 0.01606 -0.0830 0.9559 0.0064
-7.750 -0.5150 0.01918 0.01424 -0.0831 0.9547 0.0066
-7.500 -0.5007 0.01807 0.01290 -0.0807 0.9496 0.0069
-7.250 -0.4786 0.01701 0.01161 -0.0799 0.9466 0.0073
-7.000 -0.4538 0.01602 0.01041 -0.0796 0.9447 0.0076
-6.750 -0.4280 0.01508 0.00932 -0.0795 0.9432 0.0081
-6.500 -0.4001 0.01445 0.00859 -0.0799 0.9420 0.0089
-6.250 -0.3717 0.01382 0.00783 -0.0802 0.9411 0.0097
-6.000 -0.3431 0.01314 0.00703 -0.0806 0.9402 0.0106
-5.750 -0.3279 0.01271 0.00652 -0.0780 0.9345 0.0114
-5.500 -0.3021 0.01224 0.00596 -0.0776 0.9322 0.0127
-5.250 -0.2752 0.01173 0.00538 -0.0776 0.9305 0.0147
-5.000 -0.2468 0.01130 0.00488 -0.0778 0.9291 0.0172
-4.750 -0.2180 0.01084 0.00440 -0.0781 0.9279 0.0222
-4.500 -0.1878 0.01053 0.00415 -0.0788 0.9269 0.0328
-4.250 -0.1560 0.01040 0.00402 -0.0798 0.9260 0.0417
-4.000 -0.1228 0.01034 0.00389 -0.0810 0.9253 0.0470
-3.750 -0.1048 0.01023 0.00374 -0.0789 0.9201 0.0499
-3.500 -0.0771 0.01007 0.00356 -0.0789 0.9179 0.0537
-3.250 -0.0475 0.00993 0.00339 -0.0794 0.9161 0.0573
-3.000 -0.0165 0.00981 0.00321 -0.0802 0.9146 0.0595
-2.750 0.0147 0.00954 0.00291 -0.0810 0.9132 0.0609
-2.500 0.0472 0.00929 0.00265 -0.0822 0.9120 0.0623
-2.250 0.0809 0.00908 0.00243 -0.0836 0.9110 0.0638
-2.000 0.1083 0.00895 0.00228 -0.0836 0.9084 0.0651
-1.750 0.1313 0.00884 0.00217 -0.0825 0.9039 0.0662
-1.500 0.1621 0.00870 0.00202 -0.0833 0.9007 0.0680
-1.250 0.1977 0.00856 0.00187 -0.0851 0.8981 0.0708
-1.000 0.2351 0.00838 0.00173 -0.0873 0.8960 0.0778
-0.750 0.2582 0.00828 0.00167 -0.0863 0.8902 0.0874
-0.500 0.2863 0.00805 0.00160 -0.0864 0.8846 0.1371
-0.250 0.3189 0.00778 0.00151 -0.0876 0.8778 0.1975
0.000 0.3393 0.00744 0.00151 -0.0862 0.8712 0.3145
0.250 0.3649 0.00685 0.00150 -0.0860 0.8665 0.5138
0.500 0.3735 0.00626 0.00157 -0.0817 0.8589 0.7161
1.000 0.5656 0.00612 0.00205 -0.1128 0.8359 0.9910
1.250 0.6140 0.00619 0.00201 -0.1174 0.7996 0.9987
1.500 0.6372 0.00641 0.00195 -0.1162 0.7375 1.0000
1.750 0.6335 0.00708 0.00204 -0.1090 0.6136 1.0000
2.250 0.6339 0.00869 0.00261 -0.0972 0.3868 1.0000
2.500 0.6470 0.00916 0.00279 -0.0942 0.3187 1.0000
2.750 0.6592 0.00972 0.00301 -0.0910 0.2367 1.0000
3.000 0.6729 0.01027 0.00326 -0.0882 0.1696 1.0000
3.250 0.6890 0.01071 0.00351 -0.0858 0.1207 1.0000
3.500 0.7070 0.01107 0.00373 -0.0838 0.0931 1.0000
3.750 0.7265 0.01133 0.00395 -0.0821 0.0833 1.0000
4.000 0.7465 0.01157 0.00419 -0.0805 0.0768 1.0000
4.250 0.7662 0.01183 0.00443 -0.0788 0.0698 1.0000
4.500 0.7861 0.01208 0.00468 -0.0772 0.0645 1.0000
4.750 0.8063 0.01232 0.00493 -0.0757 0.0597 1.0000
5.000 0.8263 0.01256 0.00518 -0.0741 0.0542 1.0000
5.250 0.8463 0.01279 0.00543 -0.0725 0.0489 1.0000
5.500 0.8654 0.01306 0.00567 -0.0708 0.0360 1.0000
5.750 0.8825 0.01353 0.00603 -0.0687 0.0213 1.0000
6.000 0.9006 0.01392 0.00645 -0.0668 0.0172 1.0000
6.250 0.9182 0.01439 0.00693 -0.0647 0.0143 1.0000
6.500 0.9363 0.01483 0.00741 -0.0628 0.0123 1.0000
6.750 0.9542 0.01535 0.00798 -0.0609 0.0111 1.0000
7.000 0.9724 0.01582 0.00852 -0.0591 0.0102 1.0000
7.250 0.9906 0.01632 0.00906 -0.0573 0.0092 1.0000
7.500 1.0074 0.01702 0.00981 -0.0552 0.0086 1.0000
7.750 1.0254 0.01755 0.01043 -0.0534 0.0079 1.0000
8.000 1.0434 0.01810 0.01105 -0.0517 0.0073 1.0000
8.250 1.0605 0.01877 0.01179 -0.0498 0.0069 1.0000
8.500 1.0755 0.01970 0.01278 -0.0476 0.0065 1.0000
8.750 1.0920 0.02047 0.01367 -0.0456 0.0063 1.0000
9.000 1.1087 0.02124 0.01458 -0.0437 0.0057 1.0000
9.250 1.1242 0.02213 0.01560 -0.0417 0.0055 1.0000
9.500 1.1404 0.02282 0.01637 -0.0399 0.0051 1.0000
9.750 1.1549 0.02368 0.01732 -0.0378 0.0049 1.0000
10.000 1.1662 0.02497 0.01873 -0.0353 0.0047 1.0000
10.250 1.1783 0.02624 0.02019 -0.0328 0.0046 1.0000
10.500 1.1903 0.02741 0.02157 -0.0305 0.0044 1.0000
10.750 1.1989 0.02896 0.02336 -0.0276 0.0043 1.0000
11.000 1.2053 0.03068 0.02533 -0.0245 0.0041 1.0000
11.250 1.2097 0.03242 0.02730 -0.0213 0.0040 1.0000
11.500 1.2112 0.03436 0.02948 -0.0179 0.0040 1.0000
11.750 1.2117 0.03623 0.03158 -0.0146 0.0038 1.0000
12.000 1.2028 0.03912 0.03479 -0.0104 0.0039 1.0000
12.250 1.1981 0.04139 0.03730 -0.0072 0.0038 1.0000
12.500 1.1971 0.04319 0.03924 -0.0047 0.0036 1.0000
12.750 1.1879 0.04596 0.04222 -0.0019 0.0036 1.0000
13.000 1.1702 0.04987 0.04640 0.0008 0.0036 1.0000
13.250 1.1475 0.05464 0.05145 0.0027 0.0036 1.0000
13.500 1.1305 0.05911 0.05610 0.0031 0.0036 1.0000
13.750 1.0977 0.06670 0.06397 0.0015 0.0036 1.0000
14.000 1.0770 0.07384 0.07128 -0.0021 0.0036 1.0000
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Polar data table (+)
Polar graphs
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