GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 650 AIRFOIL (goe650-il) Reynolds number: 200,000 Max Cl/Cd: 79 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe650-il-200000.txt Download as CSV file: xf-goe650-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 650 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6912 0.06033 0.05614 -0.0792 1.0000 0.0563
-11.750 -0.7358 0.05492 0.05070 -0.0798 1.0000 0.0559
-11.500 -0.7826 0.05129 0.04707 -0.0782 1.0000 0.0555
-11.250 -0.8218 0.04651 0.04210 -0.0794 1.0000 0.0551
-11.000 -0.8443 0.04272 0.03803 -0.0791 1.0000 0.0553
-10.750 -0.8387 0.03852 0.03332 -0.0826 0.9967 0.0560
-10.500 -0.8145 0.03509 0.02951 -0.0866 0.9921 0.0570
-10.250 -0.7867 0.03338 0.02778 -0.0885 0.9876 0.0582
-10.000 -0.7559 0.03187 0.02613 -0.0909 0.9838 0.0595
-9.750 -0.7281 0.03035 0.02440 -0.0927 0.9795 0.0612
-9.500 -0.7013 0.02884 0.02260 -0.0940 0.9745 0.0629
-9.250 -0.6705 0.02726 0.02079 -0.0960 0.9711 0.0647
-9.000 -0.6413 0.02631 0.01987 -0.0971 0.9673 0.0665
-8.750 -0.6145 0.02545 0.01893 -0.0976 0.9618 0.0687
-8.500 -0.5813 0.02449 0.01773 -0.0992 0.9583 0.0717
-8.250 -0.5462 0.02360 0.01686 -0.1013 0.9560 0.0752
-8.000 -0.5256 0.02304 0.01625 -0.1004 0.9494 0.0787
-7.750 -0.4958 0.02223 0.01535 -0.1012 0.9454 0.0835
-7.500 -0.4607 0.02172 0.01476 -0.1029 0.9427 0.0911
-7.250 -0.4232 0.02130 0.01434 -0.1050 0.9408 0.1014
-7.000 -0.4068 0.02109 0.01416 -0.1031 0.9327 0.1096
-6.750 -0.3740 0.02090 0.01391 -0.1043 0.9293 0.1201
-6.500 -0.3375 0.02081 0.01364 -0.1060 0.9270 0.1296
-6.250 -0.2995 0.02061 0.01351 -0.1081 0.9252 0.1374
-6.000 -0.2839 0.02061 0.01333 -0.1058 0.9163 0.1429
-5.750 -0.2474 0.02014 0.01294 -0.1075 0.9130 0.1497
-5.500 -0.2057 0.01984 0.01249 -0.1099 0.9106 0.1572
-5.250 -0.1630 0.01925 0.01194 -0.1127 0.9090 0.1643
-5.000 -0.1494 0.01929 0.01194 -0.1100 0.8996 0.1699
-4.750 -0.1138 0.01891 0.01151 -0.1114 0.8968 0.1780
-4.500 -0.0753 0.01863 0.01124 -0.1133 0.8948 0.1861
-4.250 -0.0350 0.01811 0.01064 -0.1156 0.8934 0.1931
-4.000 -0.0149 0.01795 0.01052 -0.1141 0.8869 0.1981
-3.750 0.0151 0.01772 0.01023 -0.1143 0.8822 0.2052
-3.500 0.0527 0.01723 0.00978 -0.1160 0.8797 0.2128
-3.250 0.0914 0.01686 0.00939 -0.1179 0.8777 0.2219
-3.000 0.1310 0.01640 0.00898 -0.1199 0.8759 0.2320
-2.750 0.1473 0.01647 0.00901 -0.1175 0.8677 0.2407
-2.500 0.1802 0.01612 0.00877 -0.1183 0.8636 0.2522
-2.250 0.2173 0.01575 0.00845 -0.1198 0.8609 0.2664
-2.000 0.2565 0.01540 0.00816 -0.1216 0.8587 0.2840
-1.750 0.2737 0.01546 0.00827 -0.1194 0.8503 0.2986
-1.500 0.3065 0.01522 0.00810 -0.1200 0.8457 0.3185
-1.250 0.3460 0.01487 0.00779 -0.1217 0.8423 0.3416
-1.000 0.3706 0.01477 0.00775 -0.1207 0.8341 0.3605
-0.750 0.4055 0.01443 0.00742 -0.1214 0.8273 0.3815
-0.500 0.4402 0.01413 0.00713 -0.1220 0.8204 0.4014
-0.250 0.4667 0.01395 0.00699 -0.1212 0.8110 0.4183
0.000 0.5035 0.01367 0.00671 -0.1224 0.8052 0.4368
0.250 0.5244 0.01364 0.00676 -0.1206 0.7951 0.4513
0.500 0.5602 0.01339 0.00650 -0.1216 0.7888 0.4691
0.750 0.5812 0.01335 0.00654 -0.1199 0.7781 0.4837
1.000 0.6156 0.01314 0.00632 -0.1206 0.7709 0.5015
1.250 0.6371 0.01309 0.00634 -0.1190 0.7595 0.5174
1.500 0.6655 0.01296 0.00625 -0.1186 0.7500 0.5354
1.750 0.6921 0.01283 0.00617 -0.1179 0.7392 0.5544
2.000 0.7161 0.01275 0.00616 -0.1167 0.7275 0.5750
2.250 0.7440 0.01262 0.00607 -0.1162 0.7166 0.6009
2.500 0.7674 0.01249 0.00605 -0.1149 0.7035 0.6285
2.750 0.7897 0.01234 0.00604 -0.1133 0.6896 0.6632
3.000 0.8132 0.01209 0.00600 -0.1120 0.6752 0.7191
3.250 0.8738 0.01163 0.00593 -0.1185 0.6561 1.0000
3.500 0.8970 0.01171 0.00591 -0.1172 0.6382 1.0000
3.750 0.9192 0.01181 0.00590 -0.1158 0.6184 1.0000
4.000 0.9407 0.01196 0.00590 -0.1141 0.5967 1.0000
4.250 0.9606 0.01216 0.00598 -0.1122 0.5724 1.0000
4.500 0.9803 0.01245 0.00607 -0.1103 0.5478 1.0000
4.750 0.9987 0.01279 0.00626 -0.1083 0.5222 1.0000
5.000 1.0164 0.01320 0.00650 -0.1061 0.4969 1.0000
5.250 1.0329 0.01360 0.00677 -0.1038 0.4709 1.0000
5.500 1.0484 0.01402 0.00705 -0.1013 0.4448 1.0000
5.750 1.0632 0.01445 0.00736 -0.0987 0.4192 1.0000
6.000 1.0772 0.01492 0.00769 -0.0960 0.3955 1.0000
6.250 1.0909 0.01543 0.00805 -0.0933 0.3756 1.0000
6.500 1.1043 0.01595 0.00844 -0.0906 0.3581 1.0000
6.750 1.1186 0.01648 0.00887 -0.0881 0.3423 1.0000
7.000 1.1340 0.01701 0.00933 -0.0858 0.3282 1.0000
7.250 1.1500 0.01756 0.00981 -0.0837 0.3154 1.0000
7.500 1.1661 0.01817 0.01032 -0.0817 0.3042 1.0000
7.750 1.1824 0.01869 0.01083 -0.0798 0.2929 1.0000
8.000 1.1990 0.01925 0.01137 -0.0779 0.2823 1.0000
8.250 1.2148 0.01992 0.01191 -0.0760 0.2720 1.0000
8.500 1.2293 0.02039 0.01245 -0.0738 0.2614 1.0000
8.750 1.2440 0.02101 0.01304 -0.0718 0.2516 1.0000
9.000 1.2580 0.02159 0.01361 -0.0697 0.2422 1.0000
9.250 1.2729 0.02223 0.01425 -0.0677 0.2334 1.0000
9.500 1.2866 0.02289 0.01488 -0.0657 0.2252 1.0000
9.750 1.3012 0.02356 0.01559 -0.0639 0.2173 1.0000
10.000 1.3150 0.02425 0.01628 -0.0620 0.2101 1.0000
10.250 1.3298 0.02501 0.01704 -0.0603 0.2036 1.0000
10.500 1.3434 0.02571 0.01781 -0.0585 0.1970 1.0000
10.750 1.3571 0.02659 0.01859 -0.0568 0.1909 1.0000
11.000 1.3694 0.02730 0.01945 -0.0549 0.1848 1.0000
11.250 1.3811 0.02814 0.02030 -0.0531 0.1792 1.0000
11.500 1.3949 0.02906 0.02121 -0.0516 0.1743 1.0000
11.750 1.4067 0.02990 0.02219 -0.0499 0.1692 1.0000
12.000 1.4173 0.03085 0.02316 -0.0482 0.1643 1.0000
12.250 1.4284 0.03188 0.02421 -0.0466 0.1595 1.0000
12.500 1.4377 0.03289 0.02535 -0.0449 0.1543 1.0000
12.750 1.4458 0.03404 0.02652 -0.0433 0.1494 1.0000
13.000 1.4549 0.03524 0.02779 -0.0417 0.1449 1.0000
13.250 1.4627 0.03647 0.02916 -0.0403 0.1397 1.0000
13.500 1.4680 0.03793 0.03063 -0.0388 0.1348 1.0000
13.750 1.4744 0.03939 0.03222 -0.0374 0.1293 1.0000
14.000 1.4782 0.04106 0.03398 -0.0361 0.1232 1.0000
14.250 1.4811 0.04293 0.03595 -0.0349 0.1166 1.0000
14.500 1.4813 0.04513 0.03819 -0.0339 0.1091 1.0000
14.750 1.4816 0.04747 0.04063 -0.0330 0.0997 1.0000
15.000 1.4781 0.05030 0.04351 -0.0322 0.0898 1.0000
15.250 1.4723 0.05354 0.04677 -0.0316 0.0806 1.0000
15.500 1.4648 0.05711 0.05033 -0.0312 0.0741 1.0000
15.750 1.4587 0.06066 0.05394 -0.0310 0.0685 1.0000
16.000 1.4513 0.06451 0.05784 -0.0311 0.0647 1.0000
16.250 1.4457 0.06828 0.06169 -0.0314 0.0615 1.0000
16.500 1.4363 0.07265 0.06610 -0.0320 0.0592 1.0000
16.750 1.4296 0.07677 0.07031 -0.0326 0.0571 1.0000
17.000 1.4237 0.08089 0.07455 -0.0334 0.0552 1.0000
17.250 1.4165 0.08528 0.07901 -0.0344 0.0536 1.0000
17.500 1.4078 0.08989 0.08366 -0.0356 0.0522 1.0000
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Polar data table (+)
Polar graphs
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