GOE 287 AIRFOIL (goe287-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 287 AIRFOIL (goe287-il) Reynolds number: 500,000 Max Cl/Cd: 94.48 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe287-il-500000-n5.txt Download as CSV file: xf-goe287-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 287 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4258 0.12668 0.12452 0.0088 0.9021 0.0076
-10.250 -0.4251 0.12363 0.12131 0.0090 0.8540 0.0076
-10.000 -0.4216 0.12009 0.11765 0.0080 0.8311 0.0076
-9.750 -0.4174 0.11635 0.11383 0.0066 0.8161 0.0077
-9.500 -0.4135 0.11243 0.10986 0.0049 0.8043 0.0078
-9.250 -0.4102 0.10826 0.10565 0.0031 0.7938 0.0079
-9.000 -0.4079 0.10375 0.10111 0.0009 0.7842 0.0081
-8.750 -0.4046 0.09969 0.09702 -0.0012 0.7748 0.0084
-8.500 -0.3960 0.09726 0.09456 -0.0026 0.7639 0.0086
-8.250 -0.3877 0.09462 0.09189 -0.0042 0.7531 0.0089
-8.000 -0.3802 0.09169 0.08893 -0.0061 0.7423 0.0093
-7.750 -0.3745 0.08820 0.08540 -0.0085 0.7314 0.0096
-7.500 -0.3691 0.08427 0.08145 -0.0119 0.7200 0.0098
-7.250 -0.3587 0.07957 0.07671 -0.0171 0.7086 0.0101
-7.000 -0.3460 0.07381 0.07088 -0.0239 0.6976 0.0106
-6.750 -0.3301 0.06582 0.06279 -0.0333 0.6875 0.0113
-6.500 -0.3093 0.06341 0.06029 -0.0364 0.6739 0.0117
-6.250 -0.2875 0.06088 0.05766 -0.0395 0.6607 0.0122
-6.000 -0.2638 0.05680 0.05345 -0.0442 0.6492 0.0130
-5.750 -0.2317 0.04445 0.04073 -0.0557 0.6427 0.0150
-5.500 -0.2066 0.04300 0.03916 -0.0571 0.6317 0.0154
-5.250 -0.1813 0.04171 0.03777 -0.0583 0.6224 0.0160
-5.000 -0.1536 0.03871 0.03458 -0.0605 0.6146 0.0170
-4.750 -0.1188 0.02808 0.02322 -0.0650 0.6097 0.0203
-4.500 -0.0921 0.02723 0.02223 -0.0657 0.6024 0.0208
-4.250 -0.0650 0.02620 0.02106 -0.0663 0.5962 0.0213
-4.000 -0.0369 0.02456 0.01920 -0.0669 0.5902 0.0221
-3.750 -0.0083 0.02282 0.01721 -0.0675 0.5843 0.0234
-3.500 0.0211 0.02043 0.01446 -0.0680 0.5785 0.0245
-3.250 0.0504 0.01849 0.01216 -0.0683 0.5729 0.0253
-3.000 0.0794 0.01744 0.01086 -0.0686 0.5675 0.0260
-2.750 0.1083 0.01682 0.01004 -0.0688 0.5617 0.0266
-2.500 0.1372 0.01621 0.00922 -0.0690 0.5566 0.0269
-2.250 0.1663 0.01449 0.00720 -0.0694 0.5524 0.0275
-2.000 0.1951 0.01357 0.00613 -0.0697 0.5482 0.0280
-1.750 0.2238 0.01298 0.00543 -0.0699 0.5440 0.0284
-1.500 0.2525 0.01251 0.00485 -0.0701 0.5404 0.0288
-1.250 0.2813 0.01210 0.00440 -0.0703 0.5366 0.0292
-1.000 0.3101 0.01179 0.00406 -0.0705 0.5325 0.0299
-0.750 0.3388 0.01149 0.00370 -0.0707 0.5283 0.0303
-0.500 0.3676 0.01120 0.00335 -0.0709 0.5244 0.0304
-0.250 0.3965 0.01092 0.00306 -0.0711 0.5202 0.0307
0.000 0.4253 0.01071 0.00281 -0.0713 0.5159 0.0311
0.250 0.4541 0.01055 0.00262 -0.0715 0.5123 0.0317
0.500 0.4830 0.01040 0.00246 -0.0717 0.5084 0.0326
0.750 0.5120 0.01029 0.00234 -0.0720 0.5043 0.0335
1.000 0.5409 0.01021 0.00225 -0.0722 0.5004 0.0345
1.250 0.5696 0.01017 0.00218 -0.0724 0.4962 0.0354
1.500 0.5985 0.01012 0.00214 -0.0726 0.4917 0.0363
1.750 0.6274 0.01009 0.00211 -0.0729 0.4863 0.0370
2.000 0.6560 0.01010 0.00208 -0.0731 0.4804 0.0395
2.250 0.6849 0.01007 0.00208 -0.0733 0.4736 0.0438
2.500 0.7135 0.01005 0.00212 -0.0735 0.4658 0.0707
2.750 0.7360 0.00811 0.00228 -0.0729 0.4560 1.0000
3.000 0.7645 0.00822 0.00232 -0.0731 0.4410 1.0000
3.250 0.7927 0.00839 0.00237 -0.0733 0.4141 1.0000
3.500 0.8195 0.00887 0.00254 -0.0735 0.3551 1.0000
3.750 0.8462 0.00938 0.00283 -0.0737 0.3160 1.0000
4.000 0.8734 0.00975 0.00308 -0.0738 0.2956 1.0000
4.250 0.9009 0.01003 0.00330 -0.0740 0.2829 1.0000
4.500 0.9285 0.01028 0.00351 -0.0742 0.2739 1.0000
4.750 0.9559 0.01053 0.00374 -0.0743 0.2662 1.0000
5.000 0.9833 0.01077 0.00396 -0.0744 0.2586 1.0000
5.250 1.0101 0.01111 0.00424 -0.0745 0.2445 1.0000
5.500 1.0367 0.01145 0.00452 -0.0746 0.2316 1.0000
5.750 1.0632 0.01179 0.00480 -0.0747 0.2195 1.0000
6.000 1.0899 0.01207 0.00508 -0.0748 0.2086 1.0000
6.250 1.1162 0.01241 0.00537 -0.0748 0.1942 1.0000
6.500 1.1372 0.01353 0.00603 -0.0745 0.1189 1.0000
6.750 1.1531 0.01531 0.00735 -0.0736 0.0304 1.0000
7.000 1.1770 0.01587 0.00794 -0.0732 0.0212 1.0000
7.250 1.2006 0.01642 0.00851 -0.0729 0.0169 1.0000
7.500 1.2242 0.01695 0.00911 -0.0725 0.0148 1.0000
7.750 1.2476 0.01746 0.00969 -0.0721 0.0135 1.0000
8.000 1.2701 0.01803 0.01032 -0.0716 0.0122 1.0000
8.250 1.2906 0.01881 0.01116 -0.0709 0.0108 1.0000
8.500 1.3106 0.01957 0.01200 -0.0702 0.0101 1.0000
8.750 1.3305 0.02029 0.01281 -0.0694 0.0095 1.0000
9.000 1.3488 0.02110 0.01369 -0.0684 0.0089 1.0000
9.250 1.3659 0.02195 0.01461 -0.0673 0.0084 1.0000
9.500 1.3818 0.02282 0.01556 -0.0661 0.0079 1.0000
9.750 1.3937 0.02391 0.01671 -0.0645 0.0074 1.0000
10.000 1.3968 0.02534 0.01824 -0.0618 0.0071 1.0000
10.250 1.4053 0.02659 0.01959 -0.0602 0.0069 1.0000
10.500 1.4114 0.02818 0.02129 -0.0587 0.0066 1.0000
10.750 1.4165 0.03003 0.02325 -0.0575 0.0064 1.0000
11.000 1.4206 0.03213 0.02546 -0.0566 0.0062 1.0000
11.250 1.4240 0.03439 0.02783 -0.0559 0.0060 1.0000
11.500 1.4266 0.03683 0.03038 -0.0554 0.0058 1.0000
11.750 1.4287 0.03939 0.03305 -0.0550 0.0057 1.0000
12.000 1.4300 0.04210 0.03586 -0.0547 0.0055 1.0000
12.250 1.4304 0.04496 0.03881 -0.0545 0.0054 1.0000
12.500 1.4299 0.04797 0.04192 -0.0544 0.0053 1.0000
12.750 1.4283 0.05115 0.04519 -0.0543 0.0052 1.0000
13.000 1.4253 0.05451 0.04864 -0.0543 0.0051 1.0000
13.250 1.4203 0.05814 0.05237 -0.0543 0.0050 1.0000
13.500 1.4121 0.06212 0.05645 -0.0543 0.0049 1.0000
13.750 1.4082 0.06571 0.06015 -0.0544 0.0048 1.0000
14.000 1.4065 0.06917 0.06372 -0.0546 0.0047 1.0000
14.250 1.4042 0.07274 0.06742 -0.0549 0.0046 1.0000
14.500 1.4011 0.07645 0.07124 -0.0553 0.0045 1.0000
14.750 1.3982 0.08021 0.07512 -0.0558 0.0044 1.0000
15.000 1.3950 0.08406 0.07909 -0.0563 0.0043 1.0000
15.250 1.3911 0.08802 0.08317 -0.0568 0.0042 1.0000
15.500 1.3870 0.09209 0.08738 -0.0575 0.0041 1.0000
15.750 1.3829 0.09625 0.09166 -0.0583 0.0040 1.0000
16.000 1.3786 0.10052 0.09605 -0.0592 0.0040 1.0000
16.250 1.3736 0.10497 0.10063 -0.0604 0.0039 1.0000
16.500 1.3684 0.10957 0.10535 -0.0617 0.0038 1.0000
16.750 1.3628 0.11434 0.11026 -0.0633 0.0038 1.0000
17.000 1.3571 0.11927 0.11531 -0.0651 0.0037 1.0000
17.250 1.3510 0.12439 0.12056 -0.0671 0.0037 1.0000
17.500 1.3443 0.12969 0.12599 -0.0694 0.0036 1.0000
17.750 1.3374 0.13516 0.13160 -0.0719 0.0036 1.0000
18.000 1.3304 0.14082 0.13738 -0.0747 0.0036 1.0000
18.250 1.3226 0.14678 0.14348 -0.0778 0.0035 1.0000
18.500 1.3152 0.15282 0.14964 -0.0811 0.0035 1.0000
18.750 1.3067 0.15924 0.15621 -0.0848 0.0035 1.0000
19.000 1.2970 0.16609 0.16320 -0.0888 0.0035 1.0000
19.250 1.2866 0.17335 0.17060 -0.0933 0.0035 1.0000
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