GOE 563 AIRFOIL (goe563-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 563 AIRFOIL (goe563-il) Reynolds number: 500,000 Max Cl/Cd: 76.63 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe563-il-500000-n5.txt Download as CSV file: xf-goe563-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 563 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.9613 0.03978 0.03683 -0.0712 1.0000 0.0090
-12.750 -0.9816 0.03607 0.03292 -0.0691 1.0000 0.0091
-12.500 -0.9896 0.03300 0.02963 -0.0672 1.0000 0.0093
-12.250 -0.9896 0.03062 0.02705 -0.0652 1.0000 0.0095
-12.000 -0.9834 0.02882 0.02509 -0.0634 1.0000 0.0099
-11.750 -0.9751 0.02725 0.02335 -0.0614 1.0000 0.0101
-11.500 -0.9650 0.02591 0.02185 -0.0594 1.0000 0.0106
-11.250 -0.9543 0.02466 0.02044 -0.0574 1.0000 0.0109
-11.000 -0.9429 0.02349 0.01911 -0.0552 1.0000 0.0114
-10.750 -0.9306 0.02243 0.01787 -0.0531 1.0000 0.0119
-10.500 -0.9037 0.02124 0.01651 -0.0540 0.9981 0.0126
-10.250 -0.8747 0.02052 0.01573 -0.0549 0.9960 0.0135
-10.000 -0.8449 0.01999 0.01512 -0.0559 0.9940 0.0146
-9.750 -0.8173 0.01922 0.01419 -0.0565 0.9915 0.0156
-9.500 -0.7888 0.01844 0.01327 -0.0572 0.9890 0.0166
-9.250 -0.7580 0.01806 0.01287 -0.0582 0.9870 0.0175
-9.000 -0.7261 0.01783 0.01259 -0.0594 0.9854 0.0186
-8.750 -0.6973 0.01749 0.01217 -0.0599 0.9827 0.0200
-8.500 -0.6683 0.01702 0.01155 -0.0604 0.9800 0.0211
-8.250 -0.6383 0.01647 0.01088 -0.0612 0.9777 0.0220
-8.000 -0.6075 0.01593 0.01030 -0.0622 0.9759 0.0231
-7.750 -0.5750 0.01571 0.01005 -0.0634 0.9746 0.0243
-7.500 -0.5470 0.01536 0.00965 -0.0637 0.9711 0.0254
-7.250 -0.5178 0.01493 0.00912 -0.0641 0.9680 0.0266
-7.000 -0.4870 0.01456 0.00865 -0.0649 0.9655 0.0276
-6.750 -0.4555 0.01423 0.00823 -0.0658 0.9634 0.0284
-6.500 -0.4273 0.01353 0.00744 -0.0661 0.9601 0.0293
-6.250 -0.4011 0.01290 0.00676 -0.0660 0.9554 0.0305
-6.000 -0.3719 0.01246 0.00627 -0.0664 0.9518 0.0315
-5.750 -0.3413 0.01209 0.00585 -0.0671 0.9490 0.0325
-5.500 -0.3148 0.01172 0.00543 -0.0668 0.9440 0.0333
-5.250 -0.2876 0.01135 0.00501 -0.0667 0.9389 0.0340
-5.000 -0.2586 0.01099 0.00459 -0.0669 0.9349 0.0347
-4.750 -0.2319 0.01068 0.00424 -0.0667 0.9294 0.0355
-4.500 -0.2050 0.01042 0.00393 -0.0664 0.9235 0.0364
-4.250 -0.1763 0.01018 0.00363 -0.0665 0.9187 0.0371
-4.000 -0.1510 0.00990 0.00331 -0.0659 0.9114 0.0381
-3.750 -0.1237 0.00961 0.00298 -0.0657 0.9051 0.0398
-3.500 -0.0973 0.00939 0.00274 -0.0653 0.8981 0.0417
-3.250 -0.0702 0.00920 0.00253 -0.0650 0.8913 0.0438
-3.000 -0.0433 0.00904 0.00234 -0.0647 0.8846 0.0464
-2.750 -0.0165 0.00886 0.00216 -0.0644 0.8774 0.0520
-2.500 0.0102 0.00866 0.00202 -0.0641 0.8704 0.0659
-2.250 0.0368 0.00849 0.00192 -0.0638 0.8628 0.0871
-2.000 0.0638 0.00839 0.00182 -0.0635 0.8547 0.1004
-1.750 0.0906 0.00827 0.00170 -0.0631 0.8443 0.1122
-1.500 0.1170 0.00816 0.00159 -0.0627 0.8313 0.1231
-1.250 0.1432 0.00805 0.00150 -0.0622 0.8175 0.1391
-1.000 0.1690 0.00788 0.00142 -0.0617 0.8026 0.1779
-0.750 0.1943 0.00770 0.00133 -0.0611 0.7858 0.2258
-0.500 0.2175 0.00726 0.00128 -0.0603 0.7693 0.3676
-0.250 0.2422 0.00704 0.00126 -0.0596 0.7549 0.4460
0.250 0.2889 0.00649 0.00126 -0.0577 0.7277 0.6380
0.500 0.3106 0.00623 0.00129 -0.0562 0.7128 0.7389
0.750 0.3326 0.00602 0.00135 -0.0546 0.6974 0.8357
1.000 0.3634 0.00600 0.00143 -0.0548 0.6739 0.9084
1.250 0.4098 0.00618 0.00149 -0.0587 0.6373 0.9551
1.750 0.4815 0.00657 0.00160 -0.0621 0.5706 0.9840
2.000 0.5162 0.00684 0.00169 -0.0637 0.5287 0.9935
2.250 0.5502 0.00718 0.00179 -0.0652 0.4779 1.0000
2.500 0.5698 0.00756 0.00192 -0.0636 0.4227 1.0000
2.750 0.5895 0.00797 0.00208 -0.0620 0.3683 1.0000
3.000 0.6106 0.00831 0.00224 -0.0607 0.3308 1.0000
3.250 0.6326 0.00860 0.00240 -0.0596 0.3034 1.0000
3.500 0.6555 0.00882 0.00255 -0.0586 0.2847 1.0000
3.750 0.6785 0.00905 0.00272 -0.0576 0.2667 1.0000
4.000 0.7011 0.00931 0.00289 -0.0566 0.2465 1.0000
4.250 0.7234 0.00961 0.00308 -0.0555 0.2205 1.0000
4.500 0.7459 0.00990 0.00328 -0.0545 0.1982 1.0000
4.750 0.7679 0.01023 0.00350 -0.0534 0.1725 1.0000
5.000 0.7895 0.01062 0.00376 -0.0522 0.1450 1.0000
5.250 0.8116 0.01098 0.00402 -0.0512 0.1255 1.0000
5.500 0.8343 0.01129 0.00430 -0.0502 0.1141 1.0000
5.750 0.8569 0.01162 0.00459 -0.0492 0.1031 1.0000
6.000 0.8796 0.01194 0.00488 -0.0483 0.0912 1.0000
6.250 0.9018 0.01232 0.00519 -0.0473 0.0745 1.0000
6.500 0.9219 0.01289 0.00560 -0.0460 0.0485 1.0000
6.750 0.9434 0.01334 0.00601 -0.0449 0.0397 1.0000
7.000 0.9651 0.01378 0.00644 -0.0439 0.0351 1.0000
7.250 0.9874 0.01415 0.00685 -0.0429 0.0323 1.0000
7.500 1.0096 0.01453 0.00728 -0.0419 0.0300 1.0000
7.750 1.0309 0.01498 0.00775 -0.0408 0.0275 1.0000
8.000 1.0516 0.01549 0.00829 -0.0397 0.0250 1.0000
8.250 1.0736 0.01585 0.00871 -0.0387 0.0234 1.0000
8.500 1.0950 0.01626 0.00915 -0.0377 0.0211 1.0000
8.750 1.1149 0.01680 0.00970 -0.0364 0.0191 1.0000
9.000 1.1350 0.01730 0.01027 -0.0352 0.0177 1.0000
9.250 1.1551 0.01777 0.01080 -0.0340 0.0163 1.0000
9.500 1.1745 0.01829 0.01132 -0.0328 0.0146 1.0000
9.750 1.1918 0.01897 0.01204 -0.0312 0.0134 1.0000
10.000 1.2099 0.01954 0.01268 -0.0297 0.0127 1.0000
10.250 1.2270 0.02015 0.01337 -0.0281 0.0118 1.0000
10.500 1.2423 0.02080 0.01410 -0.0262 0.0112 1.0000
10.750 1.2556 0.02150 0.01485 -0.0240 0.0106 1.0000
11.000 1.2663 0.02235 0.01576 -0.0215 0.0100 1.0000
11.250 1.2761 0.02326 0.01676 -0.0190 0.0096 1.0000
11.500 1.2873 0.02409 0.01769 -0.0168 0.0093 1.0000
11.750 1.2984 0.02493 0.01863 -0.0146 0.0089 1.0000
12.000 1.3081 0.02589 0.01969 -0.0125 0.0085 1.0000
12.250 1.3173 0.02690 0.02079 -0.0104 0.0082 1.0000
12.500 1.3262 0.02794 0.02194 -0.0084 0.0079 1.0000
12.750 1.3328 0.02919 0.02328 -0.0064 0.0077 1.0000
13.000 1.3372 0.03065 0.02483 -0.0044 0.0074 1.0000
13.250 1.3400 0.03229 0.02658 -0.0025 0.0073 1.0000
13.500 1.3375 0.03446 0.02887 -0.0006 0.0070 1.0000
13.750 1.3393 0.03639 0.03093 0.0008 0.0069 1.0000
14.000 1.3393 0.03860 0.03328 0.0020 0.0068 1.0000
14.250 1.3383 0.04103 0.03585 0.0029 0.0068 1.0000
14.500 1.3355 0.04380 0.03878 0.0034 0.0067 1.0000
14.750 1.3312 0.04692 0.04204 0.0035 0.0066 1.0000
15.000 1.3268 0.05028 0.04554 0.0032 0.0065 1.0000
15.250 1.3210 0.05400 0.04942 0.0024 0.0063 1.0000
15.500 1.3099 0.05874 0.05432 0.0010 0.0063 1.0000
15.750 1.3008 0.06353 0.05926 -0.0009 0.0062 1.0000
16.000 1.2874 0.06930 0.06521 -0.0035 0.0062 1.0000
16.250 1.2733 0.07561 0.07168 -0.0067 0.0062 1.0000
16.500 1.2564 0.08270 0.07893 -0.0104 0.0061 1.0000
16.750 1.2398 0.09007 0.08645 -0.0144 0.0061 1.0000
17.000 1.2209 0.09805 0.09456 -0.0187 0.0061 1.0000
17.250 1.1993 0.10673 0.10339 -0.0235 0.0061 1.0000
17.500 1.1775 0.11569 0.11249 -0.0284 0.0062 1.0000
17.750 1.1572 0.12456 0.12150 -0.0334 0.0062 1.0000
18.000 1.1378 0.13353 0.13059 -0.0384 0.0062 1.0000
18.250 1.1159 0.14345 0.14064 -0.0441 0.0062 1.0000
18.500 1.0956 0.15330 0.15061 -0.0497 0.0063 1.0000
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