GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il) Reynolds number: 50,000 Max Cl/Cd: 15.83 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe223-il-50000-n5.txt Download as CSV file: xf-goe223-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 223 (MVA H.34) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2596 0.10927 0.10280 -0.0745 0.9678 0.0681
-10.500 -0.2598 0.10240 0.09593 -0.0797 0.9615 0.0675
-10.250 -0.2695 0.09417 0.08767 -0.0859 0.9552 0.0666
-10.000 -0.2948 0.08486 0.07830 -0.0931 0.9468 0.0654
-9.750 -0.3313 0.07647 0.06979 -0.0996 0.9356 0.0643
-9.500 -0.3672 0.07000 0.06311 -0.1047 0.9231 0.0635
-9.250 -0.3783 0.06390 0.05666 -0.1121 0.9131 0.0633
-9.000 -0.3851 0.06053 0.05304 -0.1136 0.9021 0.0635
-8.750 -0.3664 0.05686 0.04902 -0.1180 0.8966 0.0649
-8.500 -0.3629 0.05456 0.04648 -0.1179 0.8861 0.0661
-8.250 -0.3359 0.05144 0.04291 -0.1216 0.8810 0.0679
-8.000 -0.3252 0.04959 0.04077 -0.1209 0.8711 0.0688
-7.750 -0.2937 0.04739 0.03820 -0.1228 0.8660 0.0699
-7.500 -0.2757 0.04613 0.03685 -0.1216 0.8575 0.0710
-7.250 -0.2470 0.04491 0.03562 -0.1220 0.8514 0.0735
-7.000 -0.2198 0.04382 0.03439 -0.1221 0.8450 0.0764
-6.750 -0.1991 0.04297 0.03342 -0.1210 0.8363 0.0787
-6.500 -0.1653 0.04194 0.03220 -0.1214 0.8318 0.0810
-6.250 -0.1524 0.04139 0.03168 -0.1193 0.8209 0.0828
-6.000 -0.1207 0.04028 0.03054 -0.1203 0.8157 0.0864
-5.750 -0.1046 0.03966 0.02985 -0.1194 0.8050 0.0905
-5.500 -0.0720 0.03843 0.02855 -0.1213 0.7993 0.0970
-5.250 -0.0522 0.03757 0.02764 -0.1216 0.7889 0.1036
-5.000 -0.0168 0.03589 0.02593 -0.1250 0.7829 0.1160
-4.750 0.0131 0.03385 0.02420 -0.1289 0.7737 0.1509
-4.500 0.0430 0.03408 0.02538 -0.1293 0.7664 0.3406
-4.250 0.0677 0.03500 0.02606 -0.1284 0.7570 0.3823
-4.000 0.0949 0.03595 0.02684 -0.1273 0.7495 0.4135
-3.750 0.1160 0.03674 0.02752 -0.1253 0.7409 0.4316
-3.500 0.1395 0.03734 0.02800 -0.1237 0.7331 0.4489
-3.250 0.1664 0.03777 0.02830 -0.1224 0.7274 0.4660
-3.000 0.1809 0.03847 0.02895 -0.1198 0.7172 0.4790
-2.750 0.2106 0.03850 0.02887 -0.1187 0.7132 0.4911
-2.500 0.2292 0.03863 0.02880 -0.1193 0.7024 0.4997
-2.250 0.2603 0.03826 0.02827 -0.1196 0.6981 0.5034
-2.000 0.2786 0.03848 0.02838 -0.1191 0.6894 0.5071
-1.750 0.3093 0.03818 0.02788 -0.1204 0.6837 0.5125
-1.500 0.3481 0.03754 0.02699 -0.1229 0.6804 0.5182
-1.250 0.3585 0.03827 0.02769 -0.1213 0.6707 0.5212
-1.000 0.3890 0.03806 0.02734 -0.1221 0.6665 0.5256
-0.750 0.4265 0.03761 0.02668 -0.1242 0.6638 0.5316
-0.500 0.4349 0.03870 0.02773 -0.1231 0.6541 0.5357
-0.250 0.4644 0.03861 0.02755 -0.1235 0.6503 0.5398
0.000 0.5001 0.03825 0.02706 -0.1249 0.6477 0.5450
0.250 0.5032 0.03979 0.02857 -0.1233 0.6382 0.5495
0.500 0.5324 0.03989 0.02858 -0.1241 0.6346 0.5545
0.750 0.5654 0.03974 0.02837 -0.1249 0.6322 0.5595
1.250 0.5916 0.04206 0.03058 -0.1238 0.6192 0.5697
1.500 0.6225 0.04201 0.03050 -0.1242 0.6167 0.5746
2.000 0.6411 0.04546 0.03394 -0.1228 0.6041 0.5847
2.250 0.6703 0.04564 0.03407 -0.1233 0.6013 0.5904
2.500 0.7028 0.04550 0.03389 -0.1239 0.5993 0.5967
3.000 0.7121 0.05035 0.03880 -0.1224 0.5857 0.6075
3.250 0.7431 0.05022 0.03866 -0.1227 0.5835 0.6146
3.750 0.7546 0.05489 0.04339 -0.1213 0.5693 0.6262
4.000 0.7902 0.05421 0.04270 -0.1217 0.5670 0.6353
4.500 0.8081 0.05785 0.04643 -0.1200 0.5520 0.6497
4.750 0.8280 0.05857 0.04718 -0.1196 0.5461 0.6591
5.250 0.8743 0.05889 0.04757 -0.1185 0.5339 0.6800
5.750 0.8999 0.06124 0.05006 -0.1167 0.5180 0.7029
6.000 0.8999 0.06386 0.05279 -0.1155 0.5087 0.7135
6.250 0.9156 0.06484 0.05387 -0.1148 0.5023 0.7285
6.500 0.9479 0.06385 0.05300 -0.1143 0.4993 0.7503
6.750 0.9842 0.06216 0.05147 -0.1136 0.4973 0.7811
7.250 0.9413 0.07081 0.06058 -0.1091 0.4713 0.8896
7.500 0.9683 0.07055 0.06031 -0.1090 0.4659 1.0000
7.750 1.0085 0.06901 0.05869 -0.1091 0.4631 1.0000
8.250 0.9893 0.07680 0.06657 -0.1075 0.4360 1.0000
8.500 1.0192 0.07608 0.06584 -0.1071 0.4311 1.0000
9.000 1.0431 0.07870 0.06849 -0.1058 0.4136 1.0000
9.500 1.0608 0.08220 0.07208 -0.1046 0.3961 1.0000
10.500 1.0540 0.09595 0.08604 -0.1037 0.3563 1.0000
10.750 1.0741 0.09647 0.08662 -0.1032 0.3526 1.0000
11.250 1.0829 0.10194 0.09220 -0.1030 0.3383 1.0000
11.750 1.0892 0.10794 0.09833 -0.1031 0.3245 1.0000
12.000 1.1132 0.10760 0.09806 -0.1024 0.3219 1.0000
12.500 1.1102 0.11544 0.10606 -0.1033 0.3086 1.0000
13.000 1.1168 0.12131 0.11208 -0.1038 0.2948 1.0000
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Polar data table (+)
Polar graphs
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