GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 81 AIRFOIL (goe81-il) Reynolds number: 200,000 Max Cl/Cd: 89.32 at α=-0.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe81-il-200000.txt Download as CSV file: xf-goe81-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2624 0.10673 0.10340 -0.0318 1.0000 0.0274
-8.250 -0.2825 0.10708 0.10386 -0.0274 1.0000 0.0274
-8.000 -0.3053 0.10762 0.10450 -0.0226 0.9998 0.0274
-7.750 -0.2795 0.10270 0.09958 -0.0312 0.9943 0.0276
-7.500 -0.2633 0.09729 0.09416 -0.0295 0.9930 0.0280
-7.250 -0.2408 0.09299 0.08986 -0.0336 0.9878 0.0286
-7.000 -0.2130 0.08874 0.08558 -0.0399 0.9830 0.0296
-6.750 -0.1862 0.08479 0.08161 -0.0466 0.9754 0.0309
-6.500 -0.1497 0.08077 0.07754 -0.0572 0.9685 0.0324
-6.250 -0.0901 0.07653 0.07316 -0.0784 0.9600 0.0330
-6.000 -0.0755 0.07141 0.06808 -0.0766 0.9581 0.0335
-5.750 -0.0545 0.06781 0.06447 -0.0784 0.9499 0.0342
-5.500 -0.0209 0.06404 0.06065 -0.0843 0.9449 0.0357
-5.250 0.0121 0.06062 0.05717 -0.0903 0.9351 0.0377
-5.000 0.0869 0.03922 0.03573 -0.0982 0.8940 0.0405
-4.750 0.1002 0.03613 0.03262 -0.0975 0.8846 0.0413
-4.500 0.1177 0.03351 0.02995 -0.0984 0.8734 0.0424
-4.250 0.1404 0.03086 0.02720 -0.1005 0.8642 0.0441
-4.000 0.1925 0.02951 0.02541 -0.1089 0.8542 0.0486
-3.750 0.2067 0.02546 0.02137 -0.1094 0.8452 0.0494
-3.500 0.2238 0.02287 0.01876 -0.1093 0.8373 0.0505
-3.250 0.2452 0.02092 0.01676 -0.1100 0.8282 0.0522
-3.000 0.2726 0.01898 0.01467 -0.1116 0.8214 0.0553
-2.750 0.3137 0.01755 0.01281 -0.1150 0.8129 0.0602
-2.500 0.3330 0.01520 0.01049 -0.1154 0.8066 0.0618
-2.250 0.3561 0.01386 0.00912 -0.1158 0.7986 0.0654
-2.000 0.3928 0.01284 0.00765 -0.1174 0.7917 0.0733
-1.750 0.4149 0.01124 0.00609 -0.1180 0.7844 0.0755
-1.500 0.4412 0.01023 0.00498 -0.1184 0.7771 0.0806
-1.250 0.4716 0.00926 0.00374 -0.1193 0.7701 0.0888
-1.000 0.4975 0.00846 0.00288 -0.1196 0.7623 0.0954
-0.750 0.5257 0.00766 0.00190 -0.1201 0.7550 0.1058
-0.500 0.5533 0.00704 0.00112 -0.1204 0.7468 0.1198
-0.250 0.5797 0.00649 0.00049 -0.1206 0.7389 0.1377
0.000 0.1088 0.02567 0.02139 -0.0751 0.7800 0.0570
0.500 0.6836 0.01856 0.01197 -0.1278 0.7274 0.2376
0.750 0.7087 0.01705 0.01053 -0.1278 0.7164 0.2761
1.000 0.7362 0.01618 0.00958 -0.1276 0.7054 0.3082
1.250 0.7816 0.01548 0.00756 -0.1251 0.6968 0.0735
1.500 0.8083 0.01492 0.00695 -0.1245 0.6840 0.0703
1.750 0.8350 0.01457 0.00652 -0.1239 0.6709 0.0710
2.000 0.8617 0.01423 0.00612 -0.1234 0.6581 0.0710
2.250 0.8883 0.01391 0.00576 -0.1229 0.6458 0.0703
2.500 0.9150 0.01371 0.00551 -0.1224 0.6334 0.0704
2.750 0.9412 0.01357 0.00537 -0.1219 0.6196 0.0714
3.000 0.9675 0.01346 0.00525 -0.1214 0.6052 0.0740
3.250 0.9936 0.01343 0.00519 -0.1210 0.5904 0.0819
3.500 1.0196 0.01342 0.00518 -0.1204 0.5749 0.1060
3.750 1.0415 0.01213 0.00526 -0.1191 0.5594 1.0000
4.000 1.0669 0.01232 0.00531 -0.1185 0.5430 1.0000
4.250 1.0923 0.01252 0.00541 -0.1179 0.5274 1.0000
4.500 1.1175 0.01276 0.00555 -0.1174 0.5125 1.0000
4.750 1.1424 0.01301 0.00573 -0.1168 0.4975 1.0000
5.000 1.1669 0.01331 0.00592 -0.1162 0.4823 1.0000
5.250 1.1911 0.01364 0.00616 -0.1155 0.4673 1.0000
5.500 1.2152 0.01400 0.00644 -0.1149 0.4533 1.0000
5.750 1.2392 0.01437 0.00678 -0.1143 0.4401 1.0000
6.000 1.2629 0.01477 0.00712 -0.1136 0.4272 1.0000
6.250 1.2866 0.01519 0.00748 -0.1130 0.4156 1.0000
6.500 1.3104 0.01557 0.00788 -0.1124 0.4048 1.0000
6.750 1.3342 0.01593 0.00829 -0.1117 0.3942 1.0000
7.000 1.3574 0.01634 0.00870 -0.1111 0.3838 1.0000
7.250 1.3802 0.01672 0.00910 -0.1103 0.3724 1.0000
7.500 1.4027 0.01706 0.00954 -0.1095 0.3602 1.0000
7.750 1.4243 0.01743 0.00995 -0.1085 0.3462 1.0000
8.000 1.4448 0.01781 0.01036 -0.1074 0.3297 1.0000
8.250 1.4641 0.01825 0.01079 -0.1061 0.3113 1.0000
8.500 1.4828 0.01873 0.01130 -0.1048 0.2909 1.0000
8.750 1.4994 0.01935 0.01187 -0.1031 0.2675 1.0000
9.000 1.5142 0.02009 0.01254 -0.1013 0.2422 1.0000
9.250 1.5273 0.02096 0.01332 -0.0993 0.2202 1.0000
9.500 1.5404 0.02182 0.01414 -0.0972 0.2004 1.0000
9.750 1.5512 0.02272 0.01504 -0.0949 0.1837 1.0000
10.000 1.5602 0.02368 0.01597 -0.0923 0.1694 1.0000
10.250 1.5679 0.02477 0.01702 -0.0897 0.1553 1.0000
10.500 1.5753 0.02592 0.01818 -0.0872 0.1442 1.0000
10.750 1.5815 0.02722 0.01948 -0.0848 0.1351 1.0000
11.000 1.5883 0.02854 0.02088 -0.0826 0.1264 1.0000
11.250 1.5949 0.02995 0.02236 -0.0806 0.1165 1.0000
11.500 1.6001 0.03154 0.02399 -0.0786 0.1043 1.0000
11.750 1.6065 0.03312 0.02558 -0.0770 0.0803 1.0000
12.000 1.5991 0.03596 0.02817 -0.0746 0.0600 1.0000
12.250 1.5896 0.03919 0.03139 -0.0724 0.0509 1.0000
12.500 1.5820 0.04242 0.03471 -0.0707 0.0439 1.0000
12.750 1.5779 0.04545 0.03787 -0.0693 0.0389 1.0000
13.000 1.5727 0.04871 0.04122 -0.0683 0.0356 1.0000
13.250 1.5662 0.05223 0.04485 -0.0675 0.0335 1.0000
13.500 1.5622 0.05559 0.04835 -0.0669 0.0318 1.0000
13.750 1.5571 0.05913 0.05202 -0.0665 0.0304 1.0000
14.000 1.5502 0.06302 0.05601 -0.0664 0.0292 1.0000
14.250 1.5402 0.06747 0.06055 -0.0665 0.0283 1.0000
14.500 1.5299 0.07204 0.06523 -0.0668 0.0276 1.0000
14.750 1.5234 0.07623 0.06957 -0.0671 0.0269 1.0000
15.000 1.5166 0.08055 0.07402 -0.0676 0.0261 1.0000
15.250 1.5099 0.08492 0.07851 -0.0682 0.0255 1.0000
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Polar data table (+)
Polar graphs
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