GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.27 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe286-il-1000000.txt Download as CSV file: xf-goe286-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 286 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3131 0.08054 0.07910 -0.0218 1.0000 0.0181
-8.500 -0.3059 0.07783 0.07640 -0.0225 1.0000 0.0184
-8.250 -0.4168 0.08332 0.08183 -0.0194 1.0000 0.0179
-8.000 -0.4073 0.08096 0.07949 -0.0208 1.0000 0.0181
-7.500 -0.3738 0.07478 0.07329 -0.0288 0.9799 0.0188
-7.250 -0.3612 0.07116 0.06964 -0.0327 0.9644 0.0194
-7.000 -0.3489 0.06684 0.06526 -0.0372 0.9496 0.0206
-6.750 -0.3255 0.05692 0.05517 -0.0493 0.9370 0.0216
-6.500 -0.3152 0.04665 0.04467 -0.0560 0.9243 0.0221
-6.250 -0.2986 0.04500 0.04292 -0.0560 0.8996 0.0224
-6.000 -0.2804 0.04323 0.04098 -0.0561 0.8672 0.0227
-5.750 -0.2594 0.04107 0.03863 -0.0568 0.8401 0.0231
-5.500 -0.2365 0.03843 0.03579 -0.0579 0.8194 0.0239
-5.250 -0.2128 0.02571 0.02215 -0.0610 0.8100 0.0272
-5.000 -0.1884 0.02458 0.02090 -0.0611 0.7898 0.0276
-4.750 -0.1629 0.02360 0.01978 -0.0613 0.7653 0.0280
-4.500 -0.1371 0.02251 0.01848 -0.0614 0.7327 0.0286
-4.250 -0.1109 0.02129 0.01696 -0.0614 0.6884 0.0296
-4.000 -0.0815 0.02128 0.01661 -0.0611 0.6581 0.0325
-3.750 -0.0568 0.01706 0.01181 -0.0615 0.6430 0.0341
-3.500 -0.0292 0.01637 0.01105 -0.0616 0.6301 0.0348
-3.250 -0.0013 0.01574 0.01030 -0.0617 0.6197 0.0358
-3.000 0.0279 0.01298 0.00705 -0.0613 0.6113 0.0302
-2.750 0.0563 0.01196 0.00582 -0.0612 0.6023 0.0296
-2.500 0.0849 0.01141 0.00517 -0.0612 0.5936 0.0299
-2.250 0.1135 0.01094 0.00461 -0.0612 0.5849 0.0303
-2.000 0.1421 0.01051 0.00409 -0.0612 0.5747 0.0306
-1.750 0.1707 0.01014 0.00367 -0.0613 0.5641 0.0309
-1.500 0.1993 0.00985 0.00331 -0.0613 0.5505 0.0312
-1.250 0.2278 0.00962 0.00300 -0.0613 0.5321 0.0315
-1.000 0.2563 0.00944 0.00271 -0.0614 0.5073 0.0317
-0.750 0.2846 0.00936 0.00248 -0.0614 0.4711 0.0320
-0.500 0.3128 0.00935 0.00231 -0.0615 0.4393 0.0323
-0.250 0.3412 0.00939 0.00224 -0.0616 0.4160 0.0327
0.000 0.3697 0.00921 0.00196 -0.0617 0.3980 0.0337
0.250 0.3982 0.00916 0.00183 -0.0618 0.3812 0.0350
0.500 0.4266 0.00919 0.00177 -0.0619 0.3616 0.0364
0.750 0.4550 0.00926 0.00173 -0.0620 0.3415 0.0377
1.000 0.4834 0.00932 0.00171 -0.0620 0.3246 0.0392
1.250 0.5118 0.00938 0.00171 -0.0621 0.3094 0.0428
1.500 0.5401 0.00934 0.00176 -0.0623 0.2937 0.0962
1.750 0.5665 0.00823 0.00194 -0.0628 0.2772 0.6311
2.000 0.5921 0.00757 0.00203 -0.0622 0.2478 1.0000
2.250 0.6192 0.00797 0.00218 -0.0622 0.2068 1.0000
2.500 0.6447 0.00871 0.00253 -0.0621 0.1277 1.0000
2.750 0.6727 0.00888 0.00265 -0.0621 0.1240 1.0000
3.000 0.7005 0.00906 0.00278 -0.0621 0.1207 1.0000
3.250 0.7284 0.00925 0.00291 -0.0621 0.1171 1.0000
3.500 0.7562 0.00942 0.00306 -0.0621 0.1142 1.0000
3.750 0.7841 0.00956 0.00318 -0.0622 0.1134 1.0000
4.000 0.8120 0.00970 0.00331 -0.0622 0.1125 1.0000
4.250 0.8398 0.00985 0.00346 -0.0622 0.1115 1.0000
4.500 0.8674 0.01002 0.00361 -0.0622 0.1101 1.0000
4.750 0.8950 0.01020 0.00378 -0.0622 0.1086 1.0000
5.000 0.9224 0.01040 0.00396 -0.0622 0.1067 1.0000
5.250 0.9496 0.01061 0.00415 -0.0622 0.1044 1.0000
5.500 0.9767 0.01083 0.00438 -0.0622 0.1017 1.0000
5.750 1.0041 0.01100 0.00454 -0.0622 0.1003 1.0000
6.000 1.0317 0.01111 0.00465 -0.0622 0.0991 1.0000
6.250 1.0591 0.01125 0.00479 -0.0622 0.0955 1.0000
6.500 1.0858 0.01148 0.00498 -0.0622 0.0901 1.0000
6.750 1.1127 0.01168 0.00517 -0.0621 0.0848 1.0000
7.000 1.1375 0.01218 0.00549 -0.0618 0.0596 1.0000
7.250 1.1634 0.01250 0.00582 -0.0617 0.0567 1.0000
7.500 1.1888 0.01289 0.00621 -0.0614 0.0540 1.0000
7.750 1.2142 0.01325 0.00658 -0.0612 0.0516 1.0000
8.000 1.2394 0.01361 0.00697 -0.0609 0.0497 1.0000
8.250 1.2648 0.01391 0.00731 -0.0607 0.0487 1.0000
8.500 1.2902 0.01420 0.00763 -0.0605 0.0477 1.0000
8.750 1.3152 0.01451 0.00798 -0.0602 0.0460 1.0000
9.000 1.3393 0.01493 0.00842 -0.0599 0.0433 1.0000
9.250 1.3628 0.01539 0.00890 -0.0594 0.0398 1.0000
9.500 1.3882 0.01559 0.00909 -0.0592 0.0349 1.0000
9.750 1.4072 0.01649 0.00980 -0.0582 0.0171 1.0000
10.000 1.4279 0.01715 0.01050 -0.0574 0.0151 1.0000
10.250 1.4477 0.01789 0.01127 -0.0564 0.0134 1.0000
10.500 1.4684 0.01846 0.01191 -0.0556 0.0128 1.0000
10.750 1.4877 0.01912 0.01263 -0.0546 0.0122 1.0000
11.000 1.5054 0.01988 0.01346 -0.0533 0.0116 1.0000
11.250 1.5203 0.02080 0.01445 -0.0518 0.0110 1.0000
11.500 1.5298 0.02204 0.01579 -0.0495 0.0105 1.0000
11.750 1.5432 0.02278 0.01659 -0.0477 0.0103 1.0000
12.000 1.5524 0.02365 0.01754 -0.0453 0.0100 1.0000
12.250 1.5604 0.02470 0.01868 -0.0430 0.0098 1.0000
12.500 1.5677 0.02588 0.01994 -0.0410 0.0095 1.0000
12.750 1.5740 0.02724 0.02138 -0.0392 0.0092 1.0000
13.000 1.5791 0.02881 0.02303 -0.0376 0.0090 1.0000
13.250 1.5827 0.03066 0.02497 -0.0363 0.0088 1.0000
13.500 1.5836 0.03294 0.02735 -0.0353 0.0085 1.0000
13.750 1.5801 0.03589 0.03040 -0.0346 0.0084 1.0000
14.000 1.5722 0.03960 0.03424 -0.0345 0.0082 1.0000
14.250 1.5597 0.04426 0.03905 -0.0351 0.0081 1.0000
14.500 1.5472 0.04915 0.04409 -0.0361 0.0080 1.0000
14.750 1.5444 0.05281 0.04785 -0.0368 0.0079 1.0000
15.000 1.5388 0.05684 0.05198 -0.0377 0.0078 1.0000
15.250 1.5309 0.06121 0.05646 -0.0386 0.0078 1.0000
15.500 1.5216 0.06589 0.06126 -0.0398 0.0077 1.0000
15.750 1.5117 0.07077 0.06624 -0.0411 0.0077 1.0000
16.000 1.5009 0.07592 0.07150 -0.0426 0.0076 1.0000
16.250 1.4894 0.08126 0.07695 -0.0443 0.0076 1.0000
16.500 1.4784 0.08657 0.08236 -0.0460 0.0075 1.0000
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Polar data table (+)
Polar graphs
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