GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.1 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe11k-il-1000000-n5.txt Download as CSV file: xf-goe11k-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5952 0.06969 0.06799 -0.0656 0.9897 0.0038
-10.500 -0.7150 0.02941 0.02677 -0.0940 0.9753 0.0034
-10.250 -0.7099 0.02522 0.02221 -0.0928 0.9708 0.0034
-10.000 -0.6914 0.02287 0.01958 -0.0929 0.9690 0.0035
-9.750 -0.6706 0.02084 0.01728 -0.0931 0.9677 0.0036
-9.500 -0.6470 0.01927 0.01547 -0.0934 0.9669 0.0037
-9.250 -0.6367 0.01824 0.01427 -0.0903 0.9608 0.0039
-9.000 -0.6143 0.01714 0.01296 -0.0898 0.9586 0.0040
-8.750 -0.5900 0.01612 0.01177 -0.0897 0.9570 0.0040
-8.500 -0.5656 0.01499 0.01046 -0.0897 0.9557 0.0042
-8.250 -0.5392 0.01417 0.00952 -0.0898 0.9547 0.0045
-8.000 -0.5213 0.01377 0.00907 -0.0880 0.9500 0.0048
-7.750 -0.4989 0.01317 0.00836 -0.0870 0.9467 0.0050
-7.500 -0.4734 0.01255 0.00762 -0.0868 0.9445 0.0053
-7.250 -0.4461 0.01201 0.00697 -0.0870 0.9429 0.0056
-7.000 -0.4178 0.01137 0.00622 -0.0873 0.9417 0.0058
-6.750 -0.3882 0.01084 0.00562 -0.0880 0.9407 0.0063
-6.500 -0.3652 0.01046 0.00518 -0.0871 0.9370 0.0068
-6.250 -0.3399 0.01010 0.00474 -0.0867 0.9336 0.0073
-6.000 -0.3111 0.00971 0.00429 -0.0870 0.9314 0.0081
-5.750 -0.2809 0.00933 0.00387 -0.0878 0.9297 0.0091
-5.500 -0.2489 0.00902 0.00351 -0.0889 0.9282 0.0103
-5.250 -0.2166 0.00866 0.00312 -0.0901 0.9268 0.0122
-5.000 -0.1831 0.00836 0.00278 -0.0915 0.9255 0.0147
-4.750 -0.1577 0.00810 0.00252 -0.0911 0.9219 0.0187
-4.500 -0.1293 0.00784 0.00230 -0.0914 0.9188 0.0281
-4.250 -0.0978 0.00768 0.00218 -0.0924 0.9165 0.0387
-4.000 -0.0642 0.00759 0.00211 -0.0939 0.9146 0.0445
-3.750 -0.0296 0.00755 0.00204 -0.0955 0.9128 0.0471
-3.500 0.0045 0.00747 0.00192 -0.0971 0.9109 0.0485
-3.250 0.0310 0.00731 0.00176 -0.0969 0.9076 0.0520
-3.000 0.0582 0.00721 0.00165 -0.0968 0.9036 0.0542
-2.750 0.0883 0.00711 0.00152 -0.0974 0.8998 0.0553
-2.500 0.1211 0.00701 0.00138 -0.0986 0.8961 0.0560
-2.250 0.1467 0.00692 0.00128 -0.0981 0.8917 0.0567
-2.000 0.1729 0.00684 0.00119 -0.0978 0.8872 0.0573
-1.750 0.2039 0.00678 0.00107 -0.0986 0.8798 0.0580
-1.500 0.2273 0.00672 0.00100 -0.0975 0.8723 0.0586
-1.250 0.2555 0.00667 0.00093 -0.0977 0.8665 0.0594
-1.000 0.2804 0.00661 0.00088 -0.0970 0.8618 0.0622
-0.750 0.3055 0.00655 0.00083 -0.0964 0.8555 0.0652
-0.500 0.3323 0.00651 0.00080 -0.0962 0.8501 0.0695
-0.250 0.3555 0.00642 0.00077 -0.0952 0.8427 0.0870
0.000 0.3788 0.00629 0.00076 -0.0942 0.8325 0.1379
0.250 0.4018 0.00618 0.00075 -0.0931 0.8223 0.1789
0.500 0.4215 0.00596 0.00075 -0.0914 0.8080 0.2786
0.750 0.4387 0.00581 0.00076 -0.0890 0.7831 0.3669
1.250 0.4529 0.00520 0.00086 -0.0798 0.7141 0.7163
1.750 0.5570 0.00729 0.00203 -0.0924 0.3311 0.9882
2.000 0.5926 0.00814 0.00235 -0.0947 0.2028 0.9959
2.250 0.6352 0.00864 0.00256 -0.0986 0.1378 0.9997
2.500 0.6558 0.00897 0.00272 -0.0972 0.0961 1.0000
2.750 0.6756 0.00918 0.00286 -0.0955 0.0805 1.0000
3.000 0.6959 0.00936 0.00300 -0.0939 0.0725 1.0000
3.250 0.7169 0.00951 0.00314 -0.0924 0.0691 1.0000
3.500 0.7372 0.00969 0.00330 -0.0909 0.0639 1.0000
3.750 0.7582 0.00985 0.00346 -0.0894 0.0604 1.0000
4.000 0.7790 0.01001 0.00362 -0.0880 0.0569 1.0000
4.250 0.7993 0.01021 0.00379 -0.0864 0.0523 1.0000
4.500 0.8205 0.01036 0.00396 -0.0850 0.0501 1.0000
4.750 0.8412 0.01054 0.00413 -0.0836 0.0427 1.0000
5.000 0.8603 0.01083 0.00433 -0.0818 0.0281 1.0000
5.250 0.8793 0.01115 0.00461 -0.0800 0.0187 1.0000
5.500 0.8984 0.01148 0.00492 -0.0783 0.0142 1.0000
5.750 0.9175 0.01181 0.00524 -0.0765 0.0114 1.0000
6.000 0.9372 0.01208 0.00554 -0.0749 0.0102 1.0000
6.250 0.9558 0.01242 0.00589 -0.0730 0.0089 1.0000
6.500 0.9745 0.01272 0.00623 -0.0711 0.0081 1.0000
6.750 0.9929 0.01303 0.00656 -0.0693 0.0071 1.0000
7.000 1.0108 0.01343 0.00699 -0.0673 0.0066 1.0000
7.250 1.0292 0.01377 0.00737 -0.0655 0.0061 1.0000
7.500 1.0474 0.01417 0.00781 -0.0636 0.0057 1.0000
7.750 1.0659 0.01452 0.00820 -0.0619 0.0052 1.0000
8.000 1.0838 0.01499 0.00872 -0.0600 0.0049 1.0000
8.250 1.1018 0.01546 0.00924 -0.0582 0.0046 1.0000
8.500 1.1197 0.01595 0.00979 -0.0563 0.0043 1.0000
8.750 1.1378 0.01640 0.01030 -0.0546 0.0041 1.0000
9.000 1.1558 0.01689 0.01086 -0.0529 0.0038 1.0000
9.250 1.1731 0.01746 0.01149 -0.0510 0.0037 1.0000
9.500 1.1903 0.01803 0.01213 -0.0493 0.0035 1.0000
9.750 1.2053 0.01886 0.01304 -0.0471 0.0033 1.0000
10.000 1.2213 0.01953 0.01381 -0.0451 0.0032 1.0000
10.250 1.2364 0.02030 0.01467 -0.0430 0.0031 1.0000
10.500 1.2526 0.02090 0.01537 -0.0412 0.0030 1.0000
10.750 1.2665 0.02173 0.01632 -0.0389 0.0029 1.0000
11.000 1.2799 0.02260 0.01729 -0.0367 0.0028 1.0000
11.250 1.2925 0.02350 0.01834 -0.0344 0.0027 1.0000
11.500 1.3035 0.02451 0.01947 -0.0318 0.0027 1.0000
11.750 1.3153 0.02540 0.02047 -0.0296 0.0025 1.0000
12.000 1.3215 0.02677 0.02202 -0.0264 0.0026 1.0000
12.250 1.3346 0.02747 0.02279 -0.0245 0.0025 1.0000
12.500 1.3430 0.02857 0.02399 -0.0220 0.0024 1.0000
12.750 1.3472 0.03001 0.02557 -0.0190 0.0023 1.0000
13.000 1.3514 0.03140 0.02709 -0.0162 0.0022 1.0000
13.250 1.3505 0.03324 0.02912 -0.0129 0.0022 1.0000
13.500 1.3503 0.03506 0.03110 -0.0099 0.0021 1.0000
13.750 1.3445 0.03736 0.03359 -0.0067 0.0021 1.0000
14.000 1.3452 0.03919 0.03558 -0.0044 0.0021 1.0000
14.250 1.3372 0.04184 0.03842 -0.0017 0.0020 1.0000
14.500 1.3228 0.04522 0.04199 0.0009 0.0021 1.0000
14.750 1.3184 0.04784 0.04476 0.0024 0.0020 1.0000
15.000 1.3004 0.05208 0.04918 0.0036 0.0021 1.0000
15.250 1.2838 0.05671 0.05402 0.0039 0.0020 1.0000
15.500 1.2585 0.06316 0.06067 0.0025 0.0020 1.0000
15.750 1.2397 0.06972 0.06737 -0.0004 0.0020 1.0000
16.000 1.2040 0.08192 0.07977 -0.0084 0.0021 1.0000
16.250 1.1265 0.10722 0.10534 -0.0229 0.0022 1.0000
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