GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 92 AIRFOIL (goe92-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.65 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe92-il-1000000.txt Download as CSV file: xf-goe92-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 92 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1895 0.09358 0.09197 -0.0296 0.9061 0.0084
-9.000 -0.1872 0.09027 0.08862 -0.0308 0.8973 0.0084
-8.750 -0.1844 0.08691 0.08524 -0.0319 0.8894 0.0085
-8.500 -0.1809 0.08359 0.08189 -0.0329 0.8825 0.0085
-8.250 -0.1774 0.08020 0.07849 -0.0340 0.8755 0.0085
-8.000 -0.1737 0.07682 0.07509 -0.0351 0.8695 0.0085
-7.250 -0.1607 0.06649 0.06473 -0.0365 0.8501 0.0090
-7.000 -0.1558 0.06348 0.06170 -0.0377 0.8432 0.0093
-6.750 -0.1508 0.06026 0.05849 -0.0395 0.8356 0.0095
-6.500 -0.1424 0.05666 0.05485 -0.0426 0.8280 0.0097
-6.250 -0.1308 0.05277 0.05095 -0.0463 0.8197 0.0100
-6.000 -0.1588 0.06459 0.06265 -0.0525 0.8347 0.0097
-5.750 -0.1366 0.06094 0.05894 -0.0569 0.8267 0.0100
-5.500 -0.1123 0.05716 0.05509 -0.0614 0.8176 0.0106
-5.250 -0.0777 0.05271 0.05052 -0.0678 0.8085 0.0115
-5.000 -0.0470 0.04854 0.04621 -0.0724 0.7979 0.0116
-4.750 -0.0192 0.04465 0.04218 -0.0753 0.7850 0.0116
-4.500 0.0049 0.03932 0.03667 -0.0784 0.7702 0.0119
-4.250 0.0267 0.03744 0.03467 -0.0793 0.7458 0.0123
-4.000 0.0514 0.03544 0.03246 -0.0803 0.7073 0.0130
-3.750 0.0854 0.03291 0.02953 -0.0811 0.6615 0.0152
-3.250 0.1413 0.02773 0.02374 -0.0819 0.6056 0.0154
-2.750 0.1921 0.02163 0.01710 -0.0828 0.5721 0.0163
-2.500 0.2181 0.02089 0.01622 -0.0830 0.5562 0.0175
-2.250 0.2494 0.02023 0.01527 -0.0821 0.5418 0.0202
-2.000 0.2772 0.01837 0.01310 -0.0819 0.5282 0.0203
-1.750 0.3040 0.01486 0.00914 -0.0817 0.5158 0.0213
-1.500 0.3303 0.01464 0.00889 -0.0819 0.4999 0.0226
-1.250 0.3587 0.01544 0.00956 -0.0816 0.4827 0.0267
-1.000 0.3866 0.01474 0.00860 -0.0813 0.4644 0.0270
-0.750 0.4135 0.01237 0.00586 -0.0811 0.4441 0.0284
-0.500 0.4401 0.01192 0.00530 -0.0810 0.4173 0.0299
-0.250 0.4669 0.01169 0.00491 -0.0809 0.3938 0.0320
0.000 0.4946 0.01251 0.00560 -0.0807 0.3754 0.0359
1.000 0.6033 0.01025 0.00300 -0.0800 0.3386 0.0346
1.250 0.6308 0.00995 0.00268 -0.0799 0.3341 0.0340
1.500 0.6582 0.00980 0.00249 -0.0798 0.3294 0.0343
1.750 0.6855 0.00976 0.00241 -0.0797 0.3247 0.0350
2.000 0.7132 0.00971 0.00234 -0.0797 0.3216 0.0354
2.250 0.7408 0.00968 0.00230 -0.0797 0.3180 0.0357
2.500 0.7683 0.00970 0.00229 -0.0797 0.3144 0.0360
2.750 0.7955 0.00973 0.00228 -0.0796 0.3102 0.0368
3.000 0.8232 0.00973 0.00228 -0.0796 0.3074 0.0374
3.250 0.8509 0.00976 0.00229 -0.0796 0.3048 0.0395
3.500 0.8784 0.00981 0.00234 -0.0796 0.3020 0.0454
3.750 0.9038 0.00818 0.00266 -0.0798 0.2993 1.0000
4.000 0.9306 0.00835 0.00278 -0.0797 0.2960 1.0000
4.250 0.9580 0.00846 0.00288 -0.0796 0.2935 1.0000
4.500 0.9854 0.00854 0.00296 -0.0797 0.2896 1.0000
4.750 1.0121 0.00872 0.00307 -0.0796 0.2815 1.0000
5.000 1.0394 0.00881 0.00317 -0.0796 0.2776 1.0000
5.250 1.0664 0.00894 0.00327 -0.0796 0.2704 1.0000
5.500 1.0932 0.00909 0.00339 -0.0795 0.2612 1.0000
5.750 1.1196 0.00928 0.00354 -0.0795 0.2498 1.0000
6.000 1.1449 0.00960 0.00372 -0.0792 0.2260 1.0000
6.250 1.1609 0.01103 0.00457 -0.0779 0.1330 1.0000
6.500 1.1815 0.01193 0.00521 -0.0770 0.0950 1.0000
6.750 1.1976 0.01338 0.00632 -0.0755 0.0166 1.0000
7.000 1.2218 0.01380 0.00678 -0.0751 0.0139 1.0000
7.250 1.2453 0.01428 0.00734 -0.0745 0.0119 1.0000
7.500 1.2690 0.01470 0.00781 -0.0741 0.0112 1.0000
7.750 1.2920 0.01520 0.00837 -0.0735 0.0104 1.0000
8.000 1.3142 0.01575 0.00899 -0.0728 0.0097 1.0000
8.250 1.3354 0.01640 0.00970 -0.0720 0.0091 1.0000
8.500 1.3527 0.01741 0.01083 -0.0706 0.0082 1.0000
8.750 1.3688 0.01846 0.01199 -0.0691 0.0077 1.0000
9.000 1.3882 0.01912 0.01272 -0.0681 0.0074 1.0000
9.250 1.4050 0.01995 0.01364 -0.0667 0.0071 1.0000
9.500 1.4197 0.02088 0.01465 -0.0651 0.0068 1.0000
9.750 1.4320 0.02191 0.01576 -0.0632 0.0065 1.0000
10.000 1.4399 0.02295 0.01688 -0.0606 0.0063 1.0000
10.250 1.4457 0.02413 0.01814 -0.0580 0.0061 1.0000
10.500 1.4504 0.02547 0.01957 -0.0556 0.0058 1.0000
10.750 1.4529 0.02710 0.02129 -0.0534 0.0057 1.0000
11.000 1.4519 0.02918 0.02345 -0.0515 0.0055 1.0000
11.250 1.4471 0.03179 0.02616 -0.0497 0.0054 1.0000
11.500 1.4368 0.03517 0.02964 -0.0481 0.0053 1.0000
11.750 1.4224 0.03925 0.03383 -0.0469 0.0052 1.0000
12.000 1.4088 0.04341 0.03808 -0.0458 0.0050 1.0000
12.250 1.4163 0.04570 0.04048 -0.0463 0.0049 1.0000
12.500 1.4185 0.04860 0.04348 -0.0466 0.0048 1.0000
12.750 1.4169 0.05188 0.04686 -0.0466 0.0047 1.0000
13.000 1.4143 0.05521 0.05027 -0.0465 0.0046 1.0000
13.250 1.4124 0.05843 0.05357 -0.0463 0.0046 1.0000
13.500 1.4111 0.06150 0.05673 -0.0459 0.0045 1.0000
13.750 1.4109 0.06439 0.05970 -0.0453 0.0045 1.0000
14.000 1.4116 0.06723 0.06261 -0.0448 0.0044 1.0000
14.250 1.4125 0.07006 0.06552 -0.0442 0.0044 1.0000
14.500 1.4132 0.07297 0.06853 -0.0438 0.0043 1.0000
14.750 1.4140 0.07588 0.07153 -0.0431 0.0043 1.0000
15.000 1.4127 0.07936 0.07513 -0.0434 0.0041 1.0000
15.250 1.4111 0.08279 0.07868 -0.0432 0.0041 1.0000
15.500 1.4078 0.08660 0.08261 -0.0434 0.0041 1.0000
15.750 1.4027 0.09080 0.08695 -0.0438 0.0040 1.0000
16.000 1.3962 0.09523 0.09155 -0.0434 0.0043 1.0000
16.250 1.3847 0.10057 0.09704 -0.0439 0.0046 1.0000
17.500 1.0843 0.11870 0.11591 -0.0367 0.0045 1.0000
17.750 1.0707 0.12282 0.12015 -0.0385 0.0045 1.0000
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Polar data table (+)
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