GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il) Reynolds number: 50,000 Max Cl/Cd: 28.15 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe140-il-50000.txt Download as CSV file: xf-goe140-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 140 (MVA H.17) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2301 0.10666 0.10057 -0.0262 1.0000 0.1170
-8.500 -0.2405 0.10612 0.10015 -0.0277 1.0000 0.1179
-8.250 -0.3023 0.10900 0.10251 -0.0197 1.0000 0.1137
-8.000 -0.3055 0.10781 0.10143 -0.0215 1.0000 0.1166
-7.750 -0.3132 0.10779 0.10155 -0.0253 1.0000 0.1178
-7.500 -0.2992 0.10167 0.09548 -0.0225 1.0000 0.1208
-7.250 -0.2914 0.09829 0.09215 -0.0220 1.0000 0.1254
-7.000 -0.2909 0.09641 0.09038 -0.0239 1.0000 0.1301
-6.750 -0.2949 0.09653 0.09062 -0.0307 1.0000 0.1325
-6.500 -0.2849 0.09072 0.08489 -0.0243 1.0000 0.1378
-6.250 -0.2837 0.08877 0.08303 -0.0256 1.0000 0.1442
-6.000 -0.2840 0.08732 0.08168 -0.0296 1.0000 0.1477
-5.750 -0.2812 0.08365 0.07811 -0.0248 1.0000 0.1530
-5.500 -0.2799 0.08271 0.07720 -0.0289 1.0000 0.1604
-5.250 -0.2799 0.07952 0.07410 -0.0265 1.0000 0.1638
-5.000 -0.2789 0.07731 0.07195 -0.0248 1.0000 0.1706
-4.500 -0.2716 0.07310 0.06782 -0.0261 1.0000 0.1870
-4.250 -0.2673 0.07067 0.06544 -0.0263 1.0000 0.1952
-4.000 -0.2597 0.06855 0.06333 -0.0276 1.0000 0.2088
-3.750 -0.2539 0.06643 0.06126 -0.0275 1.0000 0.2249
-3.500 -0.2462 0.06468 0.05953 -0.0280 1.0000 0.2486
-3.250 0.1208 0.03739 0.03185 -0.0296 1.0000 1.0000
-3.000 0.1158 0.03711 0.03173 -0.0276 1.0000 1.0000
-2.500 -0.1680 0.05305 0.04828 -0.0222 0.9602 0.5059
-2.250 -0.1535 0.05033 0.04567 -0.0159 0.9455 0.5900
-2.000 -0.1403 0.04763 0.04307 -0.0087 0.9308 0.6655
-1.750 -0.1244 0.04474 0.04026 -0.0014 0.9164 0.7328
-1.500 -0.0840 0.04182 0.03730 -0.0046 0.8999 0.7723
-1.250 0.3026 0.03617 0.02802 -0.1080 0.8727 0.2666
-1.000 0.3599 0.03414 0.02548 -0.1121 0.8556 0.2310
-0.750 0.4120 0.03280 0.02352 -0.1145 0.8382 0.2031
-0.500 0.4562 0.03160 0.02186 -0.1155 0.8208 0.1887
-0.250 0.4877 0.03078 0.02079 -0.1150 0.7997 0.1823
0.000 0.5202 0.03008 0.01980 -0.1143 0.7807 0.1798
0.250 0.5516 0.02941 0.01888 -0.1133 0.7628 0.1849
0.500 0.5819 0.02889 0.01808 -0.1120 0.7456 0.1883
0.750 0.6091 0.02853 0.01756 -0.1107 0.7282 0.1916
1.000 0.6346 0.02828 0.01726 -0.1095 0.7108 0.1992
1.250 0.6609 0.02806 0.01700 -0.1085 0.6946 0.2182
1.500 0.6881 0.02775 0.01687 -0.1079 0.6796 0.2593
1.750 0.7105 0.02630 0.01682 -0.1055 0.6667 1.0000
2.000 0.7381 0.02678 0.01676 -0.1043 0.6536 1.0000
2.250 0.7639 0.02742 0.01705 -0.1034 0.6403 1.0000
2.500 0.7882 0.02827 0.01771 -0.1029 0.6270 1.0000
2.750 0.8121 0.02919 0.01848 -0.1025 0.6145 1.0000
3.000 0.8362 0.03014 0.01931 -0.1020 0.6033 1.0000
3.250 0.8637 0.03068 0.01967 -0.1015 0.5946 1.0000
3.500 0.8844 0.03215 0.02118 -0.1013 0.5834 1.0000
3.750 0.9069 0.03340 0.02240 -0.1011 0.5741 1.0000
4.000 0.9320 0.03430 0.02323 -0.1007 0.5660 1.0000
4.250 0.9496 0.03626 0.02528 -0.1006 0.5570 1.0000
4.500 0.9744 0.03732 0.02635 -0.1003 0.5508 1.0000
4.750 0.9873 0.04001 0.02919 -0.1005 0.5434 1.0000
5.000 1.0067 0.04180 0.03103 -0.1004 0.5373 1.0000
5.250 1.0227 0.04406 0.03337 -0.1003 0.5316 1.0000
5.500 1.0232 0.04820 0.03768 -0.1005 0.5248 1.0000
5.750 1.0437 0.04997 0.03953 -0.1003 0.5207 1.0000
6.000 1.0351 0.05547 0.04517 -0.1009 0.5173 1.0000
6.250 0.9907 0.06525 0.05503 -0.1030 0.5167 1.0000
6.500 0.9688 0.07191 0.06172 -0.1041 0.5179 1.0000
6.750 0.7549 0.09720 0.08720 -0.1163 0.6963 1.0000
7.000 0.7669 0.09959 0.08960 -0.1161 0.6880 1.0000
7.250 0.7867 0.10293 0.09294 -0.1171 0.6836 1.0000
7.500 0.7916 0.10483 0.09486 -0.1159 0.6723 1.0000
7.750 0.7951 0.10713 0.09721 -0.1149 0.6630 1.0000
8.000 0.8206 0.11046 0.10058 -0.1162 0.6558 1.0000
8.250 0.8169 0.11236 0.10251 -0.1146 0.6459 1.0000
8.500 0.8516 0.11667 0.10691 -0.1168 0.6396 1.0000
8.750 0.8496 0.11821 0.10849 -0.1151 0.6264 1.0000
9.000 0.8554 0.12047 0.11080 -0.1142 0.6129 1.0000
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Polar data table (+)
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