GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 723 AIRFOIL (goe723-il) Reynolds number: 200,000 Max Cl/Cd: 82.25 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe723-il-200000.txt Download as CSV file: xf-goe723-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 723 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3095 0.09266 0.08916 -0.0400 1.0000 0.0688
-8.250 -0.3186 0.09115 0.08774 -0.0380 1.0000 0.0706
-7.750 -0.3286 0.08116 0.07789 -0.0543 0.9848 0.0762
-7.500 -0.2989 0.07897 0.07567 -0.0536 0.9822 0.0777
-7.250 -0.2731 0.07600 0.07269 -0.0568 0.9743 0.0804
-7.000 -0.2512 0.06428 0.06089 -0.0821 0.9583 0.0888
-6.750 -0.2273 0.06340 0.06002 -0.0792 0.9510 0.0903
-6.500 -0.1985 0.05277 0.04908 -0.1002 0.9393 0.1020
-6.250 -0.1676 0.05194 0.04835 -0.0988 0.9338 0.1037
-6.000 -0.1327 0.05040 0.04680 -0.1008 0.9291 0.1090
-5.750 -0.1061 0.04488 0.04108 -0.1089 0.9169 0.1194
-5.500 -0.0791 0.04054 0.03644 -0.1151 0.9054 0.1325
-5.250 -0.0650 0.02566 0.01966 -0.1199 0.8919 0.0721
-5.000 -0.0366 0.02349 0.01666 -0.1195 0.8816 0.0639
-4.750 -0.0123 0.02137 0.01434 -0.1191 0.8705 0.0626
-4.500 0.0168 0.02016 0.01285 -0.1192 0.8620 0.0628
-4.250 0.0411 0.01918 0.01167 -0.1184 0.8509 0.0628
-4.000 0.0678 0.01818 0.01048 -0.1179 0.8416 0.0625
-3.750 0.0942 0.01733 0.00949 -0.1173 0.8322 0.0623
-3.500 0.1200 0.01665 0.00870 -0.1167 0.8232 0.0624
-3.250 0.1468 0.01603 0.00799 -0.1161 0.8147 0.0628
-3.000 0.1721 0.01554 0.00744 -0.1154 0.8059 0.0634
-2.750 0.1986 0.01511 0.00694 -0.1148 0.7978 0.0640
-2.500 0.2223 0.01451 0.00637 -0.1139 0.7895 0.0662
-2.250 0.2479 0.01414 0.00599 -0.1133 0.7818 0.0693
-2.000 0.2733 0.01390 0.00570 -0.1126 0.7740 0.0720
-1.750 0.2994 0.01370 0.00542 -0.1120 0.7662 0.0748
-1.500 0.3257 0.01343 0.00512 -0.1114 0.7594 0.0818
-1.250 0.3502 0.01304 0.00491 -0.1106 0.7514 0.1188
-1.000 0.3747 0.01237 0.00498 -0.1101 0.7453 0.3374
-0.750 0.3981 0.01233 0.00513 -0.1091 0.7370 0.4066
-0.500 0.4246 0.01231 0.00514 -0.1085 0.7303 0.4505
-0.250 0.4490 0.01231 0.00521 -0.1076 0.7223 0.4859
0.000 0.4747 0.01226 0.00521 -0.1069 0.7146 0.5240
0.250 0.4993 0.01223 0.00527 -0.1060 0.7070 0.5648
0.500 0.5239 0.01211 0.00529 -0.1050 0.6994 0.6117
0.750 0.5488 0.01189 0.00529 -0.1041 0.6933 0.6806
1.000 0.6344 0.01125 0.00519 -0.1164 0.6847 1.0000
1.250 0.6627 0.01139 0.00516 -0.1163 0.6787 1.0000
1.500 0.6873 0.01155 0.00528 -0.1156 0.6710 1.0000
1.750 0.7143 0.01168 0.00531 -0.1152 0.6643 1.0000
2.000 0.7402 0.01185 0.00542 -0.1147 0.6577 1.0000
2.250 0.7658 0.01199 0.00552 -0.1141 0.6503 1.0000
2.500 0.7935 0.01215 0.00557 -0.1139 0.6443 1.0000
2.750 0.8173 0.01230 0.00575 -0.1129 0.6362 1.0000
3.000 0.8445 0.01244 0.00581 -0.1126 0.6297 1.0000
3.250 0.8686 0.01260 0.00599 -0.1117 0.6213 1.0000
3.500 0.8952 0.01268 0.00598 -0.1112 0.6127 1.0000
3.750 0.9183 0.01277 0.00609 -0.1100 0.6018 1.0000
4.000 0.9436 0.01286 0.00613 -0.1093 0.5924 1.0000
4.250 0.9677 0.01294 0.00619 -0.1083 0.5816 1.0000
4.500 0.9911 0.01305 0.00631 -0.1072 0.5706 1.0000
4.750 1.0155 0.01316 0.00637 -0.1063 0.5600 1.0000
5.000 1.0388 0.01326 0.00647 -0.1052 0.5483 1.0000
5.250 1.0613 0.01339 0.00664 -0.1039 0.5361 1.0000
5.500 1.0843 0.01354 0.00678 -0.1028 0.5241 1.0000
5.750 1.1068 0.01368 0.00692 -0.1016 0.5111 1.0000
6.000 1.1287 0.01385 0.00706 -0.1002 0.4972 1.0000
6.250 1.1496 0.01403 0.00724 -0.0987 0.4818 1.0000
6.500 1.1699 0.01423 0.00747 -0.0971 0.4651 1.0000
6.750 1.1893 0.01446 0.00771 -0.0954 0.4463 1.0000
7.000 1.2078 0.01473 0.00798 -0.0935 0.4252 1.0000
7.250 1.2239 0.01509 0.00827 -0.0912 0.3993 1.0000
7.500 1.2361 0.01562 0.00866 -0.0883 0.3634 1.0000
7.750 1.2401 0.01651 0.00927 -0.0841 0.3102 1.0000
8.000 1.2287 0.01818 0.01032 -0.0777 0.2081 1.0000
8.250 1.2098 0.02026 0.01178 -0.0705 0.1332 1.0000
8.500 1.2062 0.02176 0.01313 -0.0659 0.1159 1.0000
8.750 1.2097 0.02295 0.01434 -0.0626 0.1072 1.0000
9.000 1.2106 0.02436 0.01574 -0.0592 0.1016 1.0000
9.250 1.2181 0.02548 0.01694 -0.0568 0.0968 1.0000
9.500 1.2229 0.02685 0.01834 -0.0543 0.0929 1.0000
9.750 1.2228 0.02868 0.02013 -0.0516 0.0895 1.0000
10.000 1.2332 0.02983 0.02138 -0.0500 0.0867 1.0000
10.250 1.2421 0.03114 0.02275 -0.0483 0.0836 1.0000
10.500 1.2499 0.03258 0.02421 -0.0467 0.0808 1.0000
10.750 1.2557 0.03428 0.02588 -0.0449 0.0781 1.0000
11.000 1.2658 0.03567 0.02734 -0.0435 0.0757 1.0000
11.250 1.2764 0.03700 0.02876 -0.0422 0.0732 1.0000
11.500 1.2866 0.03841 0.03019 -0.0409 0.0707 1.0000
11.750 1.2968 0.03987 0.03163 -0.0396 0.0682 1.0000
12.000 1.3114 0.04126 0.03303 -0.0382 0.0657 1.0000
12.250 1.3215 0.04271 0.03461 -0.0371 0.0634 1.0000
12.500 1.3320 0.04420 0.03618 -0.0360 0.0611 1.0000
12.750 1.3442 0.04563 0.03760 -0.0349 0.0588 1.0000
13.000 1.3657 0.04708 0.03903 -0.0337 0.0559 1.0000
13.250 1.3718 0.04886 0.04101 -0.0326 0.0542 1.0000
13.500 1.3816 0.05056 0.04283 -0.0315 0.0522 1.0000
13.750 1.3919 0.05226 0.04459 -0.0306 0.0503 1.0000
14.000 1.4212 0.05401 0.04625 -0.0299 0.0476 1.0000
14.250 1.4170 0.05635 0.04886 -0.0286 0.0466 1.0000
14.500 1.4164 0.05879 0.05151 -0.0276 0.0453 1.0000
14.750 1.4188 0.06117 0.05405 -0.0268 0.0439 1.0000
15.000 1.4237 0.06344 0.05643 -0.0261 0.0427 1.0000
15.250 1.4292 0.06573 0.05880 -0.0255 0.0417 1.0000
15.500 1.4470 0.06852 0.06159 -0.0247 0.0402 1.0000
15.750 1.4316 0.07220 0.06556 -0.0242 0.0398 1.0000
16.000 1.4162 0.07621 0.06987 -0.0242 0.0392 1.0000
16.250 1.4015 0.08068 0.07461 -0.0244 0.0388 1.0000
16.500 1.3861 0.08544 0.07962 -0.0251 0.0383 1.0000
16.750 1.3698 0.09059 0.08502 -0.0261 0.0379 1.0000
17.000 1.3521 0.09615 0.09081 -0.0277 0.0376 1.0000
17.250 1.3333 0.10210 0.09699 -0.0299 0.0372 1.0000
17.500 1.3105 0.10911 0.10424 -0.0328 0.0371 1.0000
17.750 1.2856 0.11685 0.11221 -0.0366 0.0370 1.0000
18.000 1.2503 0.12720 0.12282 -0.0424 0.0374 1.0000
18.250 1.2094 0.13976 0.13565 -0.0502 0.0380 1.0000
18.500 1.1671 0.15408 0.15017 -0.0595 0.0391 1.0000
18.750 1.1259 0.16989 0.16609 -0.0696 0.0399 1.0000
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