GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il) Reynolds number: 500,000 Max Cl/Cd: 107.29 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe610bm-il-500000-n5.txt Download as CSV file: xf-goe610bm-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2689 0.09236 0.09020 -0.0334 0.9404 0.0074
-7.500 -0.2600 0.09039 0.08820 -0.0341 0.9263 0.0081
-7.250 -0.2536 0.08751 0.08529 -0.0354 0.9130 0.0084
-6.750 -0.2367 0.07801 0.07572 -0.0434 0.8884 0.0069
-6.500 -0.2221 0.07407 0.07174 -0.0476 0.8765 0.0069
-6.250 -0.2045 0.06974 0.06736 -0.0527 0.8649 0.0069
-6.000 -0.1833 0.06477 0.06231 -0.0590 0.8531 0.0070
-5.750 -0.1587 0.05975 0.05723 -0.0659 0.8401 0.0072
-5.500 -0.1322 0.05593 0.05331 -0.0715 0.8272 0.0074
-5.250 -0.1028 0.05192 0.04919 -0.0774 0.8153 0.0078
-5.000 -0.0709 0.04779 0.04493 -0.0834 0.8038 0.0085
-4.750 -0.0279 0.04003 0.03692 -0.0936 0.7934 0.0096
-4.500 0.0236 0.02912 0.02548 -0.1051 0.7844 0.0107
-4.250 0.0736 0.01599 0.01092 -0.1133 0.7777 0.0152
-4.000 0.1009 0.01659 0.01152 -0.1132 0.7665 0.0158
-3.750 0.1286 0.01686 0.01175 -0.1133 0.7560 0.0166
-3.500 0.1574 0.01646 0.01117 -0.1136 0.7461 0.0182
-3.250 0.1875 0.01547 0.00985 -0.1141 0.7368 0.0212
-3.000 0.2170 0.01500 0.00916 -0.1144 0.7279 0.0225
-2.750 0.2468 0.01384 0.00772 -0.1151 0.7191 0.0244
-2.500 0.2758 0.01338 0.00713 -0.1155 0.7093 0.0256
-2.250 0.3049 0.01297 0.00658 -0.1158 0.6999 0.0269
-2.000 0.3338 0.01265 0.00614 -0.1161 0.6903 0.0285
-1.750 0.3630 0.01219 0.00553 -0.1163 0.6792 0.0296
-1.500 0.3921 0.01178 0.00499 -0.1166 0.6666 0.0304
-1.250 0.4210 0.01142 0.00451 -0.1168 0.6523 0.0309
-1.000 0.4498 0.01111 0.00408 -0.1170 0.6356 0.0312
-0.750 0.4784 0.01092 0.00376 -0.1171 0.6142 0.0319
-0.500 0.5067 0.01075 0.00344 -0.1173 0.5891 0.0322
-0.250 0.5352 0.01058 0.00313 -0.1174 0.5675 0.0321
0.000 0.5638 0.01045 0.00288 -0.1176 0.5514 0.0320
0.250 0.5923 0.01036 0.00269 -0.1178 0.5383 0.0320
0.500 0.6209 0.01030 0.00255 -0.1180 0.5271 0.0321
0.750 0.6495 0.01026 0.00244 -0.1182 0.5176 0.0323
1.000 0.6780 0.01024 0.00237 -0.1184 0.5099 0.0328
1.250 0.7065 0.01025 0.00233 -0.1186 0.5022 0.0334
1.500 0.7348 0.01028 0.00233 -0.1187 0.4954 0.0342
1.750 0.7634 0.01029 0.00229 -0.1189 0.4889 0.0401
2.250 0.8206 0.01009 0.00250 -0.1196 0.4769 0.2272
2.500 0.8487 0.00926 0.00278 -0.1203 0.4696 0.7168
3.000 0.8985 0.00896 0.00285 -0.1189 0.4511 1.0000
3.250 0.9263 0.00911 0.00295 -0.1190 0.4416 1.0000
3.500 0.9542 0.00925 0.00306 -0.1191 0.4346 1.0000
3.750 0.9821 0.00939 0.00319 -0.1192 0.4276 1.0000
4.000 1.0098 0.00954 0.00332 -0.1193 0.4195 1.0000
4.250 1.0372 0.00971 0.00347 -0.1193 0.4102 1.0000
4.500 1.0643 0.00992 0.00363 -0.1193 0.3928 1.0000
4.750 1.0906 0.01024 0.00381 -0.1192 0.3623 1.0000
5.000 1.1163 0.01064 0.00404 -0.1191 0.3260 1.0000
5.250 1.1388 0.01154 0.00450 -0.1187 0.2496 1.0000
5.500 1.1580 0.01295 0.00534 -0.1178 0.1498 1.0000
5.750 1.1797 0.01390 0.00597 -0.1173 0.0982 1.0000
6.000 1.1976 0.01536 0.00693 -0.1161 0.0204 1.0000
6.250 1.2224 0.01576 0.00738 -0.1157 0.0136 1.0000
6.500 1.2470 0.01617 0.00788 -0.1153 0.0120 1.0000
6.750 1.2708 0.01666 0.00847 -0.1148 0.0105 1.0000
7.000 1.2931 0.01733 0.00926 -0.1140 0.0089 1.0000
7.250 1.3161 0.01784 0.00984 -0.1133 0.0080 1.0000
7.500 1.3383 0.01842 0.01050 -0.1126 0.0073 1.0000
7.750 1.3595 0.01908 0.01126 -0.1117 0.0067 1.0000
8.000 1.3792 0.01985 0.01211 -0.1106 0.0062 1.0000
8.250 1.3943 0.02104 0.01340 -0.1088 0.0058 1.0000
8.500 1.4125 0.02182 0.01427 -0.1074 0.0055 1.0000
8.750 1.4300 0.02261 0.01514 -0.1060 0.0050 1.0000
9.000 1.4451 0.02351 0.01612 -0.1042 0.0046 1.0000
9.250 1.4572 0.02455 0.01724 -0.1020 0.0044 1.0000
9.500 1.4672 0.02562 0.01840 -0.0995 0.0042 1.0000
9.750 1.4723 0.02680 0.01970 -0.0963 0.0041 1.0000
10.000 1.4758 0.02823 0.02122 -0.0932 0.0039 1.0000
10.250 1.4752 0.03013 0.02323 -0.0900 0.0038 1.0000
10.500 1.4742 0.03226 0.02547 -0.0871 0.0037 1.0000
10.750 1.4767 0.03422 0.02756 -0.0849 0.0036 1.0000
11.000 1.4784 0.03640 0.02986 -0.0828 0.0035 1.0000
11.250 1.4789 0.03879 0.03238 -0.0808 0.0035 1.0000
11.500 1.4791 0.04134 0.03505 -0.0791 0.0034 1.0000
11.750 1.4790 0.04401 0.03785 -0.0774 0.0033 1.0000
12.000 1.4792 0.04674 0.04072 -0.0759 0.0032 1.0000
12.250 1.4797 0.04951 0.04362 -0.0746 0.0031 1.0000
12.500 1.4805 0.05227 0.04651 -0.0735 0.0030 1.0000
12.750 1.4808 0.05514 0.04951 -0.0727 0.0029 1.0000
13.000 1.4807 0.05811 0.05261 -0.0721 0.0028 1.0000
13.250 1.4797 0.06123 0.05585 -0.0718 0.0027 1.0000
13.500 1.4774 0.06460 0.05936 -0.0716 0.0026 1.0000
13.750 1.4745 0.06816 0.06308 -0.0717 0.0025 1.0000
14.000 1.4706 0.07197 0.06703 -0.0719 0.0025 1.0000
14.250 1.4656 0.07605 0.07125 -0.0723 0.0025 1.0000
14.500 1.4597 0.08040 0.07574 -0.0730 0.0024 1.0000
14.750 1.4530 0.08501 0.08050 -0.0739 0.0024 1.0000
15.000 1.4449 0.08993 0.08557 -0.0749 0.0024 1.0000
15.250 1.4359 0.09511 0.09089 -0.0763 0.0024 1.0000
15.500 1.4254 0.10068 0.09661 -0.0779 0.0023 1.0000
15.750 1.4141 0.10657 0.10267 -0.0798 0.0023 1.0000
16.250 1.3887 0.11938 0.11581 -0.0848 0.0023 1.0000
16.500 1.3765 0.12613 0.12274 -0.0880 0.0023 1.0000
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Polar data table (+)
Polar graphs
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