GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 611 AIRFOIL (goe611-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.87 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe611-il-1000000-n5.txt Download as CSV file: xf-goe611-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 611 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1484 0.08756 0.08509 -0.0721 0.7821 0.0054
-9.000 -0.1461 0.08343 0.08097 -0.0744 0.7769 0.0056
-8.750 -0.1459 0.07886 0.07639 -0.0771 0.7716 0.0058
-8.500 -0.1500 0.07341 0.07094 -0.0808 0.7666 0.0060
-8.250 -0.1571 0.06624 0.06377 -0.0885 0.7611 0.0062
-8.000 -0.1464 0.06172 0.05921 -0.0943 0.7557 0.0063
-7.000 -0.1390 0.01341 0.00813 -0.1132 0.7386 0.0111
-6.750 -0.1101 0.01351 0.00825 -0.1134 0.7331 0.0117
-6.500 -0.0811 0.01374 0.00850 -0.1136 0.7267 0.0121
-6.250 -0.0523 0.01394 0.00871 -0.1138 0.7209 0.0125
-6.000 -0.0263 0.01260 0.00713 -0.1138 0.7143 0.0139
-5.750 0.0014 0.01224 0.00665 -0.1138 0.7074 0.0146
-5.500 0.0305 0.01240 0.00682 -0.1141 0.6999 0.0149
-5.250 0.0590 0.01253 0.00691 -0.1142 0.6919 0.0153
-5.000 0.0876 0.01251 0.00685 -0.1144 0.6832 0.0158
-4.750 0.1154 0.01218 0.00640 -0.1145 0.6746 0.0168
-4.500 0.1429 0.01158 0.00563 -0.1145 0.6650 0.0180
-4.250 0.1708 0.01135 0.00532 -0.1146 0.6551 0.0185
-4.000 0.1990 0.01136 0.00528 -0.1147 0.6445 0.0189
-3.750 0.2273 0.01141 0.00528 -0.1149 0.6332 0.0194
-3.500 0.2553 0.01133 0.00512 -0.1150 0.6212 0.0200
-3.250 0.2827 0.01114 0.00483 -0.1150 0.6052 0.0207
-3.000 0.3102 0.01101 0.00457 -0.1149 0.5889 0.0216
-2.750 0.3375 0.01089 0.00433 -0.1149 0.5722 0.0222
-2.500 0.3651 0.01078 0.00412 -0.1149 0.5583 0.0226
-2.250 0.3926 0.01071 0.00395 -0.1149 0.5436 0.0229
-2.000 0.4196 0.01029 0.00347 -0.1149 0.5325 0.0238
-1.750 0.4471 0.01015 0.00328 -0.1150 0.5229 0.0243
-1.500 0.4750 0.01002 0.00311 -0.1151 0.5139 0.0246
-1.250 0.5027 0.00992 0.00296 -0.1152 0.5055 0.0250
-1.000 0.5306 0.00982 0.00282 -0.1153 0.4970 0.0254
-0.750 0.5584 0.00976 0.00271 -0.1154 0.4890 0.0259
-0.500 0.5863 0.00972 0.00262 -0.1156 0.4805 0.0267
-0.250 0.6141 0.00967 0.00253 -0.1157 0.4725 0.0272
0.000 0.6419 0.00965 0.00246 -0.1158 0.4636 0.0277
0.250 0.6696 0.00965 0.00242 -0.1159 0.4555 0.0282
0.500 0.6971 0.00967 0.00239 -0.1160 0.4461 0.0286
0.750 0.7248 0.00970 0.00238 -0.1161 0.4369 0.0289
1.000 0.7521 0.00976 0.00239 -0.1161 0.4272 0.0291
1.250 0.7793 0.00980 0.00238 -0.1162 0.4163 0.0298
1.500 0.8066 0.00986 0.00239 -0.1162 0.4060 0.0307
1.750 0.8334 0.00996 0.00243 -0.1162 0.3949 0.0323
2.000 0.8600 0.01008 0.00250 -0.1161 0.3832 0.0338
2.250 0.8866 0.01020 0.00257 -0.1161 0.3709 0.0355
2.750 0.9304 0.00880 0.00307 -0.1147 0.3439 0.8987
3.000 0.9590 0.00889 0.00318 -0.1150 0.3303 1.0000
3.250 0.9843 0.00913 0.00333 -0.1147 0.3165 1.0000
3.500 1.0091 0.00940 0.00350 -0.1144 0.3007 1.0000
3.750 1.0333 0.00970 0.00370 -0.1140 0.2832 1.0000
4.000 1.0569 0.01004 0.00393 -0.1134 0.2648 1.0000
4.250 1.0801 0.01040 0.00417 -0.1128 0.2459 1.0000
4.500 1.1028 0.01078 0.00443 -0.1122 0.2263 1.0000
4.750 1.1239 0.01125 0.00476 -0.1112 0.2030 1.0000
5.000 1.1362 0.01227 0.00544 -0.1088 0.1405 1.0000
5.250 1.1575 0.01267 0.00576 -0.1079 0.1280 1.0000
5.500 1.1797 0.01300 0.00605 -0.1071 0.1209 1.0000
5.750 1.2029 0.01325 0.00630 -0.1065 0.1186 1.0000
6.000 1.2255 0.01351 0.00656 -0.1058 0.1167 1.0000
6.250 1.2469 0.01383 0.00686 -0.1050 0.1140 1.0000
6.500 1.2668 0.01419 0.00719 -0.1038 0.1098 1.0000
6.750 1.2859 0.01450 0.00751 -0.1025 0.1066 1.0000
7.000 1.3057 0.01479 0.00782 -0.1013 0.1051 1.0000
7.250 1.3259 0.01508 0.00812 -0.1002 0.1041 1.0000
7.500 1.3457 0.01540 0.00847 -0.0991 0.1023 1.0000
7.750 1.3645 0.01578 0.00886 -0.0979 0.0994 1.0000
8.000 1.3813 0.01627 0.00932 -0.0964 0.0947 1.0000
8.250 1.3992 0.01672 0.00977 -0.0951 0.0902 1.0000
8.500 1.4012 0.01805 0.01086 -0.0915 0.0541 1.0000
8.750 1.3961 0.01989 0.01258 -0.0871 0.0162 1.0000
9.000 1.4103 0.02065 0.01337 -0.0856 0.0130 1.0000
9.250 1.4248 0.02141 0.01417 -0.0842 0.0115 1.0000
9.500 1.4378 0.02231 0.01510 -0.0827 0.0099 1.0000
9.750 1.4518 0.02315 0.01600 -0.0814 0.0092 1.0000
10.000 1.4649 0.02409 0.01698 -0.0801 0.0085 1.0000
10.250 1.4770 0.02513 0.01806 -0.0788 0.0078 1.0000
10.500 1.4874 0.02634 0.01932 -0.0774 0.0071 1.0000
10.750 1.4990 0.02747 0.02050 -0.0763 0.0068 1.0000
11.000 1.5100 0.02869 0.02176 -0.0751 0.0063 1.0000
11.250 1.5199 0.03002 0.02315 -0.0739 0.0059 1.0000
11.500 1.5287 0.03148 0.02465 -0.0728 0.0055 1.0000
11.750 1.5350 0.03316 0.02640 -0.0714 0.0052 1.0000
12.000 1.5427 0.03476 0.02806 -0.0703 0.0050 1.0000
12.250 1.5497 0.03646 0.02983 -0.0692 0.0048 1.0000
12.500 1.5561 0.03827 0.03171 -0.0682 0.0046 1.0000
12.750 1.5615 0.04020 0.03371 -0.0673 0.0044 1.0000
13.000 1.5663 0.04224 0.03581 -0.0664 0.0042 1.0000
13.250 1.5706 0.04439 0.03803 -0.0655 0.0040 1.0000
13.500 1.5739 0.04671 0.04041 -0.0648 0.0038 1.0000
13.750 1.5752 0.04929 0.04307 -0.0641 0.0037 1.0000
14.000 1.5747 0.05213 0.04599 -0.0634 0.0035 1.0000
14.250 1.5764 0.05480 0.04874 -0.0629 0.0034 1.0000
14.500 1.5772 0.05763 0.05166 -0.0626 0.0033 1.0000
14.750 1.5771 0.06064 0.05475 -0.0623 0.0032 1.0000
15.000 1.5760 0.06380 0.05801 -0.0621 0.0032 1.0000
15.250 1.5741 0.06710 0.06140 -0.0620 0.0031 1.0000
15.500 1.5716 0.07054 0.06493 -0.0620 0.0030 1.0000
15.750 1.5685 0.07411 0.06859 -0.0620 0.0029 1.0000
16.000 1.5648 0.07780 0.07237 -0.0622 0.0028 1.0000
16.250 1.5602 0.08165 0.07631 -0.0625 0.0028 1.0000
16.500 1.5553 0.08555 0.08029 -0.0628 0.0027 1.0000
16.750 1.5496 0.08962 0.08446 -0.0633 0.0027 1.0000
17.000 1.5435 0.09381 0.08873 -0.0639 0.0026 1.0000
17.250 1.5369 0.09811 0.09313 -0.0646 0.0026 1.0000
17.500 1.5292 0.10260 0.09772 -0.0654 0.0025 1.0000
17.750 1.5211 0.10719 0.10240 -0.0663 0.0025 1.0000
18.000 1.5118 0.11203 0.10735 -0.0675 0.0024 1.0000
18.250 1.5016 0.11711 0.11252 -0.0688 0.0024 1.0000
18.500 1.4900 0.12249 0.11801 -0.0703 0.0023 1.0000
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