GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 528 AIRFOIL (goe528-il) Reynolds number: 200,000 Max Cl/Cd: 75.49 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe528-il-200000.txt Download as CSV file: xf-goe528-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 528 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2228 0.11967 0.11622 -0.0408 1.0000 0.0424
-10.500 -0.2317 0.11852 0.11515 -0.0385 1.0000 0.0433
-10.250 -0.2433 0.11764 0.11435 -0.0366 0.9991 0.0444
-10.000 -0.2400 0.11367 0.11039 -0.0495 0.9923 0.0455
-9.750 -0.2156 0.10836 0.10507 -0.0497 0.9896 0.0461
-9.500 -0.1897 0.10452 0.10121 -0.0513 0.9863 0.0475
-9.250 -0.1694 0.10083 0.09752 -0.0555 0.9817 0.0494
-9.000 -0.1545 0.09687 0.09355 -0.0624 0.9742 0.0521
-8.750 -0.1515 0.09196 0.08866 -0.0763 0.9621 0.0532
-8.500 -0.1229 0.08783 0.08451 -0.0738 0.9608 0.0542
-8.250 -0.0977 0.08438 0.08105 -0.0763 0.9566 0.0556
-8.000 -0.0771 0.08085 0.07750 -0.0806 0.9487 0.0578
-7.750 -0.0630 0.07513 0.07172 -0.1007 0.9332 0.0619
-7.500 -0.0403 0.07040 0.06699 -0.1015 0.9293 0.0631
-7.250 -0.0172 0.06803 0.06460 -0.1010 0.9212 0.0647
-7.000 0.0086 0.06458 0.06110 -0.1060 0.9130 0.0673
-6.750 0.0132 0.05807 0.05416 -0.1245 0.8915 0.0728
-6.500 0.0301 0.05487 0.05109 -0.1219 0.8832 0.0738
-6.250 0.0465 0.05319 0.04942 -0.1201 0.8737 0.0751
-6.000 0.0637 0.05124 0.04741 -0.1202 0.8639 0.0774
-5.750 0.0738 0.04621 0.04186 -0.1273 0.8502 0.0858
-5.500 0.0911 0.04396 0.03971 -0.1260 0.8414 0.0872
-5.250 0.1089 0.04233 0.03806 -0.1251 0.8315 0.0892
-5.000 0.1268 0.04040 0.03602 -0.1250 0.8212 0.0932
-4.750 0.1461 0.03679 0.03197 -0.1271 0.8123 0.1014
-4.500 0.1644 0.03527 0.03046 -0.1261 0.8015 0.1039
-4.250 0.1862 0.03326 0.02799 -0.1267 0.7925 0.1161
-4.000 0.2062 0.03158 0.02639 -0.1258 0.7821 0.1192
-3.750 0.2281 0.03016 0.02463 -0.1256 0.7723 0.1327
-3.500 0.2556 0.02255 0.01563 -0.1241 0.7645 0.0711
-3.250 0.2795 0.02092 0.01372 -0.1232 0.7546 0.0696
-3.000 0.3059 0.01974 0.01222 -0.1226 0.7457 0.0698
-2.750 0.3305 0.01867 0.01094 -0.1217 0.7349 0.0694
-2.500 0.3575 0.01775 0.00975 -0.1211 0.7261 0.0692
-2.250 0.3830 0.01703 0.00886 -0.1203 0.7155 0.0698
-2.000 0.4093 0.01646 0.00814 -0.1196 0.7058 0.0709
-1.750 0.4362 0.01606 0.00758 -0.1190 0.6967 0.0729
-1.500 0.4608 0.01536 0.00692 -0.1183 0.6866 0.0758
-1.250 0.4879 0.01497 0.00646 -0.1178 0.6786 0.0788
-1.000 0.5124 0.01468 0.00616 -0.1169 0.6684 0.0825
-0.750 0.5386 0.01431 0.00574 -0.1164 0.6606 0.0884
-0.500 0.5633 0.01409 0.00554 -0.1156 0.6512 0.1000
-0.250 0.5883 0.01351 0.00520 -0.1149 0.6439 0.1630
0.000 0.6034 0.01226 0.00533 -0.1128 0.6355 0.5700
0.250 0.6741 0.01155 0.00520 -0.1211 0.6269 1.0000
0.500 0.6982 0.01169 0.00521 -0.1202 0.6184 1.0000
0.750 0.7242 0.01186 0.00520 -0.1197 0.6117 1.0000
1.000 0.7480 0.01201 0.00527 -0.1188 0.6035 1.0000
1.250 0.7746 0.01220 0.00527 -0.1184 0.5970 1.0000
1.500 0.7980 0.01237 0.00541 -0.1174 0.5890 1.0000
1.750 0.8239 0.01256 0.00545 -0.1169 0.5823 1.0000
2.000 0.8483 0.01276 0.00560 -0.1162 0.5751 1.0000
2.250 0.8734 0.01295 0.00570 -0.1156 0.5680 1.0000
2.500 0.8990 0.01318 0.00584 -0.1151 0.5616 1.0000
2.750 0.9230 0.01338 0.00600 -0.1143 0.5541 1.0000
3.000 0.9500 0.01363 0.00611 -0.1140 0.5480 1.0000
3.250 0.9726 0.01383 0.00634 -0.1130 0.5404 1.0000
3.500 0.9982 0.01405 0.00648 -0.1125 0.5338 1.0000
3.750 1.0222 0.01430 0.00671 -0.1118 0.5268 1.0000
4.000 1.0465 0.01452 0.00689 -0.1111 0.5196 1.0000
4.250 1.0722 0.01479 0.00709 -0.1107 0.5133 1.0000
4.500 1.0946 0.01500 0.00734 -0.1097 0.5056 1.0000
4.750 1.1207 0.01525 0.00749 -0.1093 0.4993 1.0000
5.000 1.1424 0.01550 0.00780 -0.1082 0.4918 1.0000
5.250 1.1668 0.01572 0.00799 -0.1076 0.4851 1.0000
5.500 1.1904 0.01601 0.00828 -0.1069 0.4784 1.0000
5.750 1.2129 0.01624 0.00853 -0.1059 0.4711 1.0000
6.000 1.2382 0.01652 0.00875 -0.1055 0.4649 1.0000
6.250 1.2583 0.01676 0.00909 -0.1042 0.4571 1.0000
6.500 1.2828 0.01702 0.00929 -0.1036 0.4508 1.0000
6.750 1.3034 0.01731 0.00968 -0.1024 0.4435 1.0000
7.000 1.3258 0.01757 0.00993 -0.1015 0.4366 1.0000
7.250 1.3474 0.01788 0.01027 -0.1005 0.4295 1.0000
7.500 1.3672 0.01811 0.01054 -0.0991 0.4213 1.0000
7.750 1.3870 0.01840 0.01085 -0.0978 0.4133 1.0000
8.000 1.4057 0.01864 0.01111 -0.0962 0.4049 1.0000
8.250 1.4242 0.01897 0.01148 -0.0947 0.3968 1.0000
8.500 1.4427 0.01928 0.01182 -0.0932 0.3891 1.0000
8.750 1.4605 0.01967 0.01225 -0.0917 0.3814 1.0000
9.000 1.4767 0.02000 0.01260 -0.0898 0.3732 1.0000
9.250 1.4919 0.02041 0.01306 -0.0878 0.3651 1.0000
9.500 1.5067 0.02080 0.01347 -0.0858 0.3575 1.0000
9.750 1.5194 0.02126 0.01399 -0.0834 0.3500 1.0000
10.000 1.5315 0.02171 0.01448 -0.0810 0.3427 1.0000
10.250 1.5440 0.02224 0.01505 -0.0787 0.3355 1.0000
10.500 1.5542 0.02278 0.01565 -0.0761 0.3281 1.0000
10.750 1.5658 0.02338 0.01627 -0.0739 0.3209 1.0000
11.000 1.5744 0.02402 0.01700 -0.0714 0.3137 1.0000
11.250 1.5872 0.02469 0.01766 -0.0695 0.3073 1.0000
11.500 1.5928 0.02547 0.01860 -0.0669 0.2999 1.0000
11.750 1.6032 0.02624 0.01933 -0.0649 0.2929 1.0000
12.000 1.6066 0.02722 0.02048 -0.0623 0.2856 1.0000
12.250 1.6141 0.02816 0.02137 -0.0602 0.2782 1.0000
12.500 1.6141 0.02941 0.02281 -0.0576 0.2697 1.0000
12.750 1.6158 0.03074 0.02415 -0.0554 0.2611 1.0000
13.000 1.6157 0.03226 0.02577 -0.0533 0.2520 1.0000
13.250 1.6163 0.03390 0.02749 -0.0515 0.2433 1.0000
13.500 1.6156 0.03572 0.02933 -0.0497 0.2349 1.0000
13.750 1.6154 0.03766 0.03141 -0.0483 0.2259 1.0000
14.000 1.6121 0.03993 0.03372 -0.0468 0.2167 1.0000
14.250 1.6069 0.04251 0.03636 -0.0456 0.2066 1.0000
14.500 1.6015 0.04530 0.03926 -0.0446 0.1955 1.0000
14.750 1.5926 0.04860 0.04261 -0.0438 0.1828 1.0000
15.000 1.5812 0.05238 0.04642 -0.0433 0.1691 1.0000
15.250 1.5672 0.05667 0.05071 -0.0431 0.1541 1.0000
15.500 1.5503 0.06151 0.05553 -0.0432 0.1383 1.0000
15.750 1.5324 0.06670 0.06069 -0.0436 0.1231 1.0000
16.000 1.5139 0.07216 0.06611 -0.0443 0.1115 1.0000
16.250 1.4963 0.07764 0.07158 -0.0451 0.1032 1.0000
16.500 1.4808 0.08297 0.07693 -0.0460 0.0969 1.0000
16.750 1.4653 0.08840 0.08235 -0.0472 0.0920 1.0000
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