GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 81 AIRFOIL (goe81-il) Reynolds number: 200,000 Max Cl/Cd: 83.38 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe81-il-200000-n5.txt Download as CSV file: xf-goe81-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2453 0.10961 0.10610 -0.0327 1.0000 0.0219
-9.000 -0.2431 0.10736 0.10391 -0.0328 1.0000 0.0224
-8.750 -0.2420 0.10530 0.10191 -0.0331 0.9992 0.0226
-8.500 -0.2264 0.10216 0.09877 -0.0393 0.9886 0.0229
-8.000 -0.1957 0.09430 0.09091 -0.0454 0.9686 0.0233
-7.750 -0.1795 0.09078 0.08738 -0.0481 0.9579 0.0237
-7.500 -0.1620 0.08740 0.08399 -0.0517 0.9466 0.0242
-7.250 -0.1427 0.08398 0.08054 -0.0561 0.9358 0.0249
-7.000 -0.1225 0.08058 0.07711 -0.0609 0.9247 0.0259
-6.750 -0.0925 0.07742 0.07387 -0.0718 0.9116 0.0273
-6.500 -0.0627 0.07390 0.07025 -0.0813 0.9005 0.0275
-6.250 -0.0417 0.07010 0.06638 -0.0851 0.8912 0.0276
-6.000 -0.0319 0.06682 0.06310 -0.0833 0.8823 0.0279
-5.750 -0.0153 0.06394 0.06017 -0.0843 0.8733 0.0284
-5.500 0.0041 0.06130 0.05748 -0.0865 0.8624 0.0294
-5.250 0.0278 0.05854 0.05465 -0.0900 0.8513 0.0309
-5.000 0.0633 0.05553 0.05149 -0.0968 0.8402 0.0328
-4.750 0.1088 0.05253 0.04820 -0.1055 0.8291 0.0334
-4.500 0.1333 0.04899 0.04456 -0.1080 0.8186 0.0337
-4.250 0.1477 0.04622 0.04180 -0.1076 0.8089 0.0344
-4.000 0.1693 0.04403 0.03954 -0.1085 0.7987 0.0356
-3.750 0.1970 0.04175 0.03715 -0.1107 0.7882 0.0371
-3.500 0.2284 0.03942 0.03464 -0.1134 0.7784 0.0389
-3.250 0.2771 0.03771 0.03244 -0.1180 0.7683 0.0413
-3.000 0.3019 0.03447 0.02911 -0.1195 0.7584 0.0420
-2.750 0.3238 0.03246 0.02706 -0.1200 0.7484 0.0431
-2.500 0.3497 0.03094 0.02543 -0.1208 0.7384 0.0453
-2.250 0.3907 0.03024 0.02423 -0.1224 0.7302 0.0509
-2.000 0.4175 0.02747 0.02135 -0.1236 0.7222 0.0518
-1.750 0.4430 0.02585 0.01968 -0.1243 0.7141 0.0531
-1.500 0.4706 0.02462 0.01832 -0.1248 0.7059 0.0553
-1.250 0.5049 0.02378 0.01703 -0.1254 0.6983 0.0627
-0.750 0.5586 0.02123 0.01436 -0.1263 0.6829 0.0681
-0.250 0.6235 0.01786 0.01011 -0.1261 0.6682 0.0402
0.000 0.6518 0.01697 0.00904 -0.1261 0.6596 0.0391
0.250 0.6800 0.01624 0.00811 -0.1259 0.6501 0.0383
0.750 0.7353 0.01514 0.00665 -0.1254 0.6291 0.0377
1.000 0.7625 0.01476 0.00615 -0.1251 0.6185 0.0384
1.500 0.8165 0.01425 0.00545 -0.1245 0.5970 0.0404
1.750 0.8433 0.01399 0.00516 -0.1242 0.5855 0.0404
2.000 0.8698 0.01379 0.00492 -0.1238 0.5729 0.0406
2.250 0.8962 0.01364 0.00475 -0.1235 0.5583 0.0410
2.500 0.9224 0.01355 0.00464 -0.1231 0.5417 0.0414
2.750 0.9485 0.01344 0.00451 -0.1228 0.5226 0.0425
3.000 0.9739 0.01347 0.00446 -0.1224 0.5014 0.0446
3.250 0.9986 0.01361 0.00448 -0.1218 0.4796 0.0484
3.500 1.0232 0.01380 0.00455 -0.1212 0.4612 0.0506
3.750 1.0482 0.01399 0.00466 -0.1206 0.4475 0.0547
4.000 1.0730 0.01420 0.00484 -0.1201 0.4358 0.0722
4.250 1.0940 0.01312 0.00515 -0.1189 0.4241 1.0000
4.500 1.1186 0.01344 0.00537 -0.1183 0.4118 1.0000
4.750 1.1430 0.01377 0.00561 -0.1178 0.4003 1.0000
5.000 1.1671 0.01413 0.00588 -0.1172 0.3896 1.0000
5.250 1.1918 0.01442 0.00616 -0.1167 0.3782 1.0000
5.500 1.2161 0.01474 0.00645 -0.1162 0.3674 1.0000
5.750 1.2400 0.01508 0.00676 -0.1156 0.3572 1.0000
6.000 1.2642 0.01539 0.00709 -0.1150 0.3462 1.0000
6.250 1.2876 0.01573 0.00742 -0.1144 0.3333 1.0000
6.500 1.3106 0.01610 0.00777 -0.1137 0.3196 1.0000
6.750 1.3334 0.01648 0.00816 -0.1130 0.3070 1.0000
7.000 1.3557 0.01688 0.00856 -0.1122 0.2945 1.0000
7.250 1.3773 0.01731 0.00899 -0.1113 0.2814 1.0000
7.500 1.3984 0.01778 0.00945 -0.1103 0.2673 1.0000
7.750 1.4180 0.01833 0.00999 -0.1092 0.2496 1.0000
8.000 1.4352 0.01905 0.01060 -0.1077 0.2246 1.0000
8.250 1.4503 0.01989 0.01131 -0.1060 0.1973 1.0000
8.500 1.4633 0.02086 0.01213 -0.1040 0.1676 1.0000
8.750 1.4759 0.02183 0.01300 -0.1020 0.1476 1.0000
9.000 1.4876 0.02275 0.01387 -0.0998 0.1358 1.0000
9.250 1.4999 0.02354 0.01469 -0.0976 0.1281 1.0000
9.500 1.5105 0.02448 0.01565 -0.0953 0.1214 1.0000
9.750 1.5230 0.02532 0.01656 -0.0934 0.1147 1.0000
10.000 1.5315 0.02645 0.01772 -0.0911 0.1064 1.0000
10.250 1.5445 0.02730 0.01868 -0.0894 0.0990 1.0000
10.500 1.5556 0.02833 0.01978 -0.0877 0.0886 1.0000
10.750 1.5576 0.03010 0.02136 -0.0853 0.0640 1.0000
11.000 1.5604 0.03189 0.02313 -0.0831 0.0558 1.0000
11.250 1.5626 0.03381 0.02509 -0.0811 0.0496 1.0000
11.500 1.5680 0.03552 0.02692 -0.0795 0.0416 1.0000
11.750 1.5686 0.03774 0.02914 -0.0777 0.0257 1.0000
12.000 1.5647 0.04049 0.03184 -0.0760 0.0209 1.0000
12.250 1.5638 0.04306 0.03449 -0.0746 0.0191 1.0000
12.500 1.5622 0.04581 0.03735 -0.0734 0.0179 1.0000
12.750 1.5595 0.04877 0.04044 -0.0723 0.0169 1.0000
13.000 1.5584 0.05165 0.04348 -0.0715 0.0162 1.0000
13.250 1.5560 0.05476 0.04676 -0.0709 0.0156 1.0000
13.500 1.5519 0.05814 0.05031 -0.0705 0.0150 1.0000
13.750 1.5465 0.06180 0.05413 -0.0702 0.0145 1.0000
14.000 1.5398 0.06578 0.05827 -0.0702 0.0141 1.0000
14.250 1.5319 0.07005 0.06270 -0.0704 0.0139 1.0000
14.500 1.5228 0.07463 0.06744 -0.0709 0.0136 1.0000
14.750 1.5124 0.07957 0.07254 -0.0717 0.0134 1.0000
15.000 1.5008 0.08482 0.07795 -0.0727 0.0132 1.0000
15.250 1.4887 0.09032 0.08360 -0.0740 0.0130 1.0000
15.500 1.4761 0.09604 0.08946 -0.0755 0.0129 1.0000
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Polar data table (+)
Polar graphs
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