GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il) Reynolds number: 200,000 Max Cl/Cd: 83.07 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe610bm-il-200000.txt Download as CSV file: xf-goe610bm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610-B MOD. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2980 0.09192 0.08880 -0.0251 1.0000 0.0293
-6.750 -0.3083 0.09073 0.08769 -0.0228 1.0000 0.0296
-6.500 -0.3204 0.08975 0.08679 -0.0203 1.0000 0.0300
-6.250 -0.3085 0.08688 0.08395 -0.0250 0.9971 0.0311
-6.000 -0.2526 0.08194 0.07891 -0.0449 0.9895 0.0324
-5.750 -0.2061 0.07645 0.07332 -0.0577 0.9845 0.0327
-5.500 -0.1863 0.06909 0.06597 -0.0621 0.9800 0.0335
-5.250 -0.1691 0.06566 0.06255 -0.0615 0.9753 0.0353
-5.000 -0.1317 0.06137 0.05820 -0.0686 0.9717 0.0380
-4.750 -0.0831 0.05630 0.05299 -0.0795 0.9677 0.0417
-4.500 -0.0104 0.05033 0.04658 -0.0965 0.9613 0.0448
-4.250 0.0103 0.04537 0.04171 -0.0984 0.9570 0.0470
-4.000 0.0410 0.04259 0.03886 -0.1014 0.9496 0.0510
-3.750 0.0937 0.03744 0.03326 -0.1101 0.9437 0.0600
-3.500 0.1189 0.03524 0.03108 -0.1111 0.9349 0.0636
-3.250 0.1608 0.03173 0.02711 -0.1155 0.9278 0.0745
-3.000 0.1843 0.03001 0.02542 -0.1156 0.9173 0.0798
-2.750 0.2138 0.02800 0.02318 -0.1167 0.9079 0.0932
-2.500 0.2427 0.02616 0.02111 -0.1174 0.8987 0.1069
-2.250 0.2699 0.02470 0.01951 -0.1177 0.8876 0.1225
-2.000 0.2973 0.02353 0.01815 -0.1180 0.8769 0.1475
-1.500 0.3719 0.01773 0.01072 -0.1178 0.8575 0.0738
-1.250 0.3999 0.01655 0.00937 -0.1173 0.8457 0.0700
-1.000 0.4277 0.01569 0.00829 -0.1168 0.8335 0.0701
-0.750 0.4553 0.01495 0.00738 -0.1162 0.8208 0.0702
-0.500 0.4829 0.01422 0.00652 -0.1156 0.8076 0.0693
-0.250 0.5103 0.01365 0.00585 -0.1150 0.7935 0.0694
0.000 0.5377 0.01321 0.00533 -0.1145 0.7783 0.0704
0.250 0.5651 0.01289 0.00493 -0.1141 0.7623 0.0719
0.500 0.5927 0.01253 0.00453 -0.1138 0.7459 0.0758
0.750 0.6203 0.01240 0.00431 -0.1135 0.7291 0.0835
1.000 0.6481 0.01230 0.00410 -0.1132 0.7124 0.0928
1.250 0.6694 0.01024 0.00408 -0.1119 0.6962 1.0000
1.500 0.6972 0.01041 0.00400 -0.1116 0.6791 1.0000
1.750 0.7249 0.01058 0.00399 -0.1114 0.6629 1.0000
2.000 0.7525 0.01075 0.00401 -0.1113 0.6478 1.0000
2.250 0.7802 0.01093 0.00406 -0.1112 0.6339 1.0000
2.500 0.8079 0.01112 0.00415 -0.1111 0.6211 1.0000
2.750 0.8355 0.01132 0.00424 -0.1111 0.6094 1.0000
3.000 0.8631 0.01155 0.00436 -0.1110 0.5986 1.0000
3.250 0.8908 0.01177 0.00454 -0.1110 0.5876 1.0000
3.500 0.9182 0.01201 0.00473 -0.1109 0.5764 1.0000
3.750 0.9453 0.01226 0.00491 -0.1108 0.5643 1.0000
4.000 0.9721 0.01253 0.00509 -0.1106 0.5517 1.0000
4.250 0.9991 0.01283 0.00531 -0.1104 0.5409 1.0000
4.500 1.0262 0.01308 0.00561 -0.1103 0.5301 1.0000
4.750 1.0531 0.01337 0.00590 -0.1102 0.5197 1.0000
5.000 1.0798 0.01366 0.00618 -0.1101 0.5090 1.0000
5.250 1.1059 0.01392 0.00642 -0.1098 0.4956 1.0000
5.500 1.1316 0.01411 0.00666 -0.1094 0.4800 1.0000
5.750 1.1573 0.01430 0.00688 -0.1091 0.4645 1.0000
6.000 1.1825 0.01444 0.00707 -0.1086 0.4454 1.0000
6.250 1.2073 0.01463 0.00725 -0.1081 0.4242 1.0000
6.500 1.2319 0.01483 0.00750 -0.1076 0.3991 1.0000
6.750 1.2553 0.01514 0.00774 -0.1070 0.3599 1.0000
7.000 1.2773 0.01569 0.00812 -0.1062 0.3103 1.0000
7.250 1.2925 0.01710 0.00893 -0.1047 0.2127 1.0000
7.500 1.3073 0.01866 0.01004 -0.1032 0.1492 1.0000
7.750 1.3251 0.01981 0.01101 -0.1019 0.1112 1.0000
8.000 1.3415 0.02105 0.01199 -0.1005 0.0675 1.0000
8.250 1.3516 0.02287 0.01349 -0.0982 0.0295 1.0000
8.500 1.3685 0.02390 0.01464 -0.0965 0.0270 1.0000
8.750 1.3840 0.02500 0.01589 -0.0947 0.0255 1.0000
9.000 1.3964 0.02630 0.01734 -0.0925 0.0239 1.0000
9.250 1.4033 0.02789 0.01915 -0.0896 0.0225 1.0000
9.500 1.4076 0.02943 0.02085 -0.0864 0.0219 1.0000
9.750 1.4094 0.03102 0.02259 -0.0829 0.0216 1.0000
10.000 1.4106 0.03286 0.02456 -0.0798 0.0214 1.0000
10.250 1.4117 0.03489 0.02672 -0.0771 0.0213 1.0000
10.500 1.4130 0.03707 0.02902 -0.0746 0.0212 1.0000
10.750 1.4152 0.03933 0.03139 -0.0723 0.0211 1.0000
11.000 1.4190 0.04162 0.03379 -0.0702 0.0211 1.0000
11.250 1.4251 0.04388 0.03616 -0.0681 0.0211 1.0000
11.500 1.4346 0.04612 0.03850 -0.0661 0.0213 1.0000
11.750 1.4483 0.04845 0.04097 -0.0642 0.0215 1.0000
12.000 1.4602 0.05092 0.04361 -0.0625 0.0215 1.0000
12.250 1.4668 0.05351 0.04643 -0.0609 0.0212 1.0000
12.500 1.4713 0.05641 0.04955 -0.0593 0.0211 1.0000
12.750 1.4771 0.06008 0.05348 -0.0577 0.0215 1.0000
13.000 1.4940 0.06378 0.05736 -0.0563 0.0225 1.0000
13.250 1.4904 0.06598 0.05979 -0.0549 0.0230 1.0000
13.500 1.4789 0.06974 0.06401 -0.0537 0.0243 1.0000
13.750 1.4558 0.07576 0.07052 -0.0532 0.0258 1.0000
14.000 1.4366 0.08175 0.07684 -0.0533 0.0269 1.0000
14.250 1.4175 0.08789 0.08325 -0.0542 0.0277 1.0000
14.500 1.3979 0.09429 0.08987 -0.0556 0.0283 1.0000
14.750 1.3777 0.10112 0.09689 -0.0576 0.0288 1.0000
15.000 1.3672 0.10705 0.10317 -0.0598 0.0318 1.0000
15.250 1.3428 0.11499 0.11132 -0.0643 0.0319 1.0000
15.500 1.3197 0.12335 0.11987 -0.0695 0.0319 1.0000
15.750 1.2982 0.13211 0.12878 -0.0752 0.0318 1.0000
16.000 1.2776 0.14141 0.13822 -0.0816 0.0316 1.0000
16.250 1.2573 0.15149 0.14842 -0.0887 0.0314 1.0000
16.500 1.2370 0.16248 0.15950 -0.0965 0.0311 1.0000
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Polar data table (+)
Polar graphs
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