GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.32 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe173-il-1000000-n5.txt Download as CSV file: xf-goe173-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 173 (ALBATROS 6020) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1886 0.08641 0.08417 -0.0453 0.7896 0.0041
-7.500 -0.1805 0.08334 0.08102 -0.0472 0.7697 0.0041
-7.250 -0.1719 0.08024 0.07786 -0.0496 0.7538 0.0042
-7.000 -0.1582 0.07667 0.07424 -0.0534 0.7409 0.0043
-6.750 -0.1420 0.07237 0.06989 -0.0585 0.7303 0.0045
-6.250 -0.1024 0.06437 0.06179 -0.0690 0.7096 0.0046
-6.000 -0.0787 0.06005 0.05741 -0.0750 0.7001 0.0046
-5.750 -0.0515 0.05506 0.05234 -0.0819 0.6911 0.0046
-5.500 -0.0206 0.04964 0.04684 -0.0895 0.6823 0.0048
-5.250 0.0089 0.04623 0.04333 -0.0943 0.6729 0.0050
-4.750 0.1046 0.01456 0.00986 -0.1193 0.6637 0.0078
-4.500 0.1323 0.01193 0.00675 -0.1198 0.6538 0.0088
-4.250 0.1597 0.01023 0.00464 -0.1201 0.6439 0.0098
-4.000 0.1877 0.01027 0.00465 -0.1199 0.6310 0.0111
-3.750 0.2155 0.01040 0.00473 -0.1198 0.6179 0.0122
-3.500 0.2432 0.00992 0.00408 -0.1198 0.6054 0.0139
-3.250 0.2712 0.01030 0.00446 -0.1197 0.5927 0.0147
-3.000 0.2989 0.01050 0.00460 -0.1196 0.5783 0.0156
-2.750 0.3266 0.01038 0.00436 -0.1195 0.5644 0.0172
-2.500 0.3545 0.01029 0.00413 -0.1194 0.5520 0.0188
-2.250 0.3823 0.01034 0.00409 -0.1193 0.5408 0.0193
-1.750 0.4378 0.00988 0.00349 -0.1194 0.5192 0.0213
-1.500 0.4656 0.00976 0.00330 -0.1194 0.5081 0.0222
-1.250 0.4934 0.00967 0.00313 -0.1193 0.4961 0.0232
-1.000 0.5210 0.00954 0.00291 -0.1193 0.4827 0.0239
-0.750 0.5485 0.00941 0.00267 -0.1192 0.4661 0.0244
-0.500 0.5757 0.00934 0.00248 -0.1191 0.4433 0.0247
-0.250 0.6026 0.00935 0.00233 -0.1189 0.4137 0.0250
0.000 0.6290 0.00945 0.00227 -0.1187 0.3809 0.0255
0.250 0.6559 0.00948 0.00216 -0.1186 0.3566 0.0256
0.750 0.7103 0.00953 0.00204 -0.1184 0.3276 0.0262
1.000 0.7377 0.00956 0.00203 -0.1183 0.3186 0.0266
1.500 0.7927 0.00961 0.00198 -0.1183 0.3042 0.0285
1.750 0.8201 0.00966 0.00199 -0.1182 0.2978 0.0298
2.000 0.8476 0.00971 0.00203 -0.1182 0.2929 0.0307
2.250 0.8750 0.00977 0.00207 -0.1181 0.2879 0.0314
2.500 0.9022 0.00986 0.00214 -0.1180 0.2828 0.0321
2.750 0.9295 0.00994 0.00222 -0.1180 0.2788 0.0332
3.000 0.9567 0.01001 0.00229 -0.1179 0.2748 0.0345
3.250 0.9838 0.01012 0.00239 -0.1179 0.2702 0.0354
3.750 1.0333 0.00879 0.00288 -0.1172 0.2630 1.0000
4.000 1.0604 0.00892 0.00300 -0.1172 0.2598 1.0000
4.250 1.0873 0.00907 0.00313 -0.1171 0.2566 1.0000
4.500 1.1141 0.00923 0.00327 -0.1170 0.2533 1.0000
4.750 1.1407 0.00939 0.00343 -0.1168 0.2486 1.0000
5.000 1.1672 0.00957 0.00358 -0.1167 0.2413 1.0000
5.250 1.1933 0.00977 0.00375 -0.1165 0.2345 1.0000
5.500 1.2195 0.00997 0.00393 -0.1163 0.2268 1.0000
5.750 1.2451 0.01021 0.00413 -0.1161 0.2166 1.0000
6.000 1.2699 0.01054 0.00437 -0.1157 0.1998 1.0000
6.250 1.2928 0.01104 0.00470 -0.1151 0.1707 1.0000
6.500 1.3009 0.01314 0.00610 -0.1123 0.0554 1.0000
6.750 1.3192 0.01415 0.00692 -0.1109 0.0137 1.0000
7.000 1.3431 0.01450 0.00730 -0.1104 0.0104 1.0000
7.250 1.3667 0.01487 0.00770 -0.1098 0.0089 1.0000
7.500 1.3892 0.01534 0.00820 -0.1091 0.0071 1.0000
7.750 1.4122 0.01572 0.00863 -0.1084 0.0064 1.0000
8.000 1.4345 0.01616 0.00910 -0.1077 0.0057 1.0000
8.250 1.4557 0.01669 0.00966 -0.1068 0.0050 1.0000
8.500 1.4766 0.01722 0.01024 -0.1059 0.0046 1.0000
8.750 1.4975 0.01771 0.01077 -0.1049 0.0041 1.0000
9.000 1.5177 0.01822 0.01132 -0.1039 0.0037 1.0000
9.250 1.5368 0.01881 0.01196 -0.1028 0.0034 1.0000
9.500 1.5527 0.01962 0.01285 -0.1011 0.0031 1.0000
9.750 1.5699 0.02026 0.01356 -0.0996 0.0030 1.0000
10.000 1.5854 0.02098 0.01434 -0.0979 0.0028 1.0000
10.250 1.5973 0.02173 0.01518 -0.0956 0.0027 1.0000
10.500 1.6076 0.02256 0.01608 -0.0931 0.0025 1.0000
10.750 1.6170 0.02347 0.01707 -0.0906 0.0024 1.0000
11.000 1.6254 0.02447 0.01816 -0.0881 0.0023 1.0000
11.250 1.6328 0.02558 0.01936 -0.0857 0.0022 1.0000
11.500 1.6396 0.02680 0.02066 -0.0835 0.0021 1.0000
11.750 1.6445 0.02826 0.02221 -0.0813 0.0020 1.0000
12.000 1.6459 0.03013 0.02417 -0.0792 0.0019 1.0000
12.250 1.6410 0.03276 0.02694 -0.0772 0.0018 1.0000
12.500 1.6438 0.03489 0.02917 -0.0760 0.0018 1.0000
12.750 1.6450 0.03733 0.03172 -0.0751 0.0018 1.0000
13.000 1.6449 0.04002 0.03452 -0.0744 0.0017 1.0000
13.250 1.6419 0.04317 0.03780 -0.0739 0.0017 1.0000
13.500 1.6370 0.04666 0.04141 -0.0736 0.0016 1.0000
13.750 1.6301 0.05050 0.04538 -0.0734 0.0016 1.0000
14.000 1.6215 0.05469 0.04969 -0.0735 0.0016 1.0000
14.250 1.6115 0.05915 0.05430 -0.0739 0.0015 1.0000
14.500 1.6004 0.06395 0.05923 -0.0744 0.0015 1.0000
14.750 1.5887 0.06899 0.06439 -0.0752 0.0015 1.0000
15.000 1.5759 0.07431 0.06984 -0.0762 0.0015 1.0000
15.250 1.5625 0.07990 0.07554 -0.0774 0.0015 1.0000
15.500 1.5500 0.08548 0.08125 -0.0787 0.0014 1.0000
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Polar data table (+)
Polar graphs
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