GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 81 AIRFOIL (goe81-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.74 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe81-il-1000000.txt Download as CSV file: xf-goe81-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 81 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1311 0.08814 0.08654 -0.0498 0.9392 0.0136
-9.000 -0.1245 0.08538 0.08369 -0.0504 0.9183 0.0139
-8.750 -0.1187 0.08264 0.08089 -0.0509 0.9046 0.0142
-8.500 -0.1129 0.07981 0.07802 -0.0515 0.8935 0.0147
-8.250 -0.1071 0.07688 0.07504 -0.0522 0.8836 0.0153
-8.000 -0.1017 0.07367 0.07181 -0.0538 0.8742 0.0159
-7.750 -0.1749 0.08584 0.08399 -0.0492 0.9004 0.0148
-7.500 -0.1652 0.08303 0.08115 -0.0512 0.8881 0.0157
-7.250 -0.1489 0.07952 0.07758 -0.0577 0.8771 0.0160
-7.000 -0.1293 0.07565 0.07364 -0.0649 0.8672 0.0160
-6.750 -0.1110 0.07150 0.06947 -0.0698 0.8578 0.0161
-6.500 -0.0991 0.06862 0.06655 -0.0695 0.8490 0.0162
-6.250 -0.0817 0.06600 0.06389 -0.0717 0.8387 0.0164
-6.000 -0.0614 0.06335 0.06120 -0.0748 0.8282 0.0167
-5.750 -0.0390 0.06062 0.05840 -0.0784 0.8173 0.0170
-5.500 -0.0146 0.05779 0.05550 -0.0823 0.8051 0.0178
-5.250 0.0277 0.05359 0.05116 -0.0918 0.7921 0.0192
-5.000 0.0626 0.04972 0.04715 -0.0980 0.7789 0.0193
-4.750 0.0928 0.04640 0.04370 -0.1019 0.7652 0.0193
-4.500 0.1130 0.04290 0.04011 -0.1038 0.7516 0.0196
-4.250 0.1360 0.04093 0.03806 -0.1051 0.7377 0.0198
-4.000 0.1625 0.03890 0.03592 -0.1071 0.7246 0.0201
-3.500 0.2215 0.03455 0.03133 -0.1116 0.7013 0.0216
-3.250 0.2631 0.03181 0.02834 -0.1148 0.6912 0.0229
-2.750 0.3270 0.02557 0.02169 -0.1186 0.6731 0.0233
-2.500 0.3528 0.02410 0.02013 -0.1195 0.6653 0.0235
-2.250 0.3804 0.02284 0.01879 -0.1203 0.6589 0.0239
-2.000 0.4087 0.02160 0.01743 -0.1210 0.6521 0.0244
-1.750 0.4382 0.02024 0.01595 -0.1216 0.6461 0.0251
-1.500 0.4690 0.01874 0.01428 -0.1221 0.6399 0.0265
-1.250 0.5017 0.01760 0.01281 -0.1219 0.6339 0.0275
-1.000 0.5320 0.01496 0.00990 -0.1228 0.6284 0.0280
-0.750 0.5598 0.01413 0.00899 -0.1231 0.6211 0.0284
-0.500 0.5879 0.01349 0.00828 -0.1234 0.6134 0.0290
-0.250 0.6162 0.01290 0.00757 -0.1235 0.6052 0.0301
0.000 0.6453 0.01296 0.00745 -0.1232 0.5971 0.0328
0.250 0.6742 0.01146 0.00572 -0.1235 0.5884 0.0340
0.500 0.7022 0.01100 0.00525 -0.1236 0.5792 0.0349
0.750 0.7301 0.01069 0.00485 -0.1236 0.5691 0.0363
1.000 0.7580 0.01062 0.00469 -0.1235 0.5563 0.0388
1.250 0.7858 0.01006 0.00402 -0.1235 0.5406 0.0422
1.500 0.8131 0.00988 0.00377 -0.1234 0.5188 0.0443
1.750 0.8396 0.01006 0.00380 -0.1231 0.4891 0.0478
2.000 0.8663 0.00983 0.00334 -0.1226 0.4600 0.0396
2.250 0.8931 0.00944 0.00276 -0.1222 0.4377 0.0332
2.500 0.9198 0.00939 0.00264 -0.1220 0.4217 0.0333
2.750 0.9468 0.00936 0.00257 -0.1219 0.4091 0.0334
3.000 0.9740 0.00932 0.00250 -0.1218 0.3985 0.0343
3.250 1.0011 0.00937 0.00251 -0.1217 0.3885 0.0350
3.500 1.0284 0.00940 0.00253 -0.1216 0.3800 0.0356
3.750 1.0553 0.00950 0.00259 -0.1215 0.3706 0.0369
4.000 1.0825 0.00957 0.00265 -0.1214 0.3621 0.0389
4.250 1.1091 0.00970 0.00273 -0.1212 0.3506 0.0415
4.500 1.1359 0.00973 0.00293 -0.1211 0.3379 0.1958
4.750 1.1582 0.00866 0.00325 -0.1205 0.3251 1.0000
5.000 1.1841 0.00890 0.00340 -0.1202 0.3095 1.0000
5.250 1.2098 0.00916 0.00358 -0.1199 0.2937 1.0000
5.500 1.2351 0.00944 0.00378 -0.1196 0.2762 1.0000
5.750 1.2589 0.00987 0.00406 -0.1190 0.2498 1.0000
6.000 1.2818 0.01039 0.00439 -0.1183 0.2191 1.0000
6.250 1.3037 0.01099 0.00479 -0.1175 0.1841 1.0000
6.500 1.3231 0.01183 0.00535 -0.1163 0.1392 1.0000
6.750 1.3464 0.01225 0.00570 -0.1157 0.1276 1.0000
7.000 1.3705 0.01258 0.00601 -0.1152 0.1211 1.0000
7.250 1.3943 0.01292 0.00632 -0.1146 0.1160 1.0000
7.500 1.4176 0.01330 0.00668 -0.1140 0.1093 1.0000
7.750 1.4420 0.01355 0.00695 -0.1136 0.1060 1.0000
8.000 1.4651 0.01391 0.00729 -0.1129 0.1002 1.0000
8.250 1.4882 0.01425 0.00763 -0.1123 0.0942 1.0000
8.500 1.5053 0.01510 0.00824 -0.1108 0.0617 1.0000
8.750 1.5248 0.01570 0.00880 -0.1097 0.0536 1.0000
9.000 1.5458 0.01614 0.00926 -0.1087 0.0493 1.0000
9.250 1.5643 0.01676 0.00987 -0.1074 0.0423 1.0000
9.500 1.5773 0.01776 0.01070 -0.1053 0.0212 1.0000
9.750 1.5914 0.01860 0.01153 -0.1032 0.0160 1.0000
10.000 1.6052 0.01933 0.01231 -0.1011 0.0141 1.0000
10.250 1.6189 0.01994 0.01298 -0.0990 0.0135 1.0000
10.500 1.6312 0.02066 0.01376 -0.0967 0.0129 1.0000
10.750 1.6420 0.02149 0.01466 -0.0943 0.0123 1.0000
11.000 1.6507 0.02251 0.01575 -0.0918 0.0117 1.0000
11.250 1.6557 0.02383 0.01717 -0.0890 0.0111 1.0000
11.500 1.6649 0.02493 0.01834 -0.0870 0.0108 1.0000
11.750 1.6744 0.02605 0.01954 -0.0852 0.0106 1.0000
12.000 1.6826 0.02734 0.02091 -0.0833 0.0103 1.0000
12.250 1.6899 0.02875 0.02240 -0.0816 0.0100 1.0000
12.500 1.6961 0.03031 0.02403 -0.0799 0.0096 1.0000
12.750 1.7012 0.03202 0.02582 -0.0783 0.0093 1.0000
13.000 1.7044 0.03397 0.02785 -0.0768 0.0091 1.0000
13.250 1.7040 0.03637 0.03035 -0.0753 0.0088 1.0000
13.500 1.6987 0.03937 0.03347 -0.0738 0.0086 1.0000
13.750 1.6869 0.04323 0.03747 -0.0724 0.0084 1.0000
14.000 1.6832 0.04638 0.04073 -0.0716 0.0083 1.0000
14.250 1.6842 0.04904 0.04348 -0.0711 0.0082 1.0000
14.500 1.6830 0.05205 0.04659 -0.0706 0.0081 1.0000
14.750 1.6797 0.05542 0.05006 -0.0704 0.0080 1.0000
15.000 1.6756 0.05896 0.05371 -0.0702 0.0079 1.0000
15.250 1.6697 0.06283 0.05769 -0.0703 0.0078 1.0000
15.500 1.6635 0.06687 0.06183 -0.0705 0.0076 1.0000
15.750 1.6553 0.07127 0.06634 -0.0709 0.0076 1.0000
16.000 1.6467 0.07582 0.07100 -0.0715 0.0075 1.0000
16.250 1.6377 0.08058 0.07587 -0.0723 0.0074 1.0000
16.500 1.6278 0.08558 0.08098 -0.0733 0.0073 1.0000
16.750 1.6179 0.09067 0.08617 -0.0744 0.0072 1.0000
17.000 1.6076 0.09588 0.09148 -0.0757 0.0071 1.0000
17.250 1.5972 0.10120 0.09691 -0.0771 0.0071 1.0000
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Polar data table (+)
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