GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.06 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe118-il-1000000.txt Download as CSV file: xf-goe118-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 118 (MVA MK.7) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.250 0.5989 0.00759 0.00119 -0.1206 0.5772 0.1121
0.500 0.6269 0.00757 0.00117 -0.1207 0.5688 0.1183
0.750 0.6547 0.00760 0.00117 -0.1208 0.5606 0.1244
1.250 0.7106 0.00750 0.00122 -0.1213 0.5459 0.1929
1.500 0.7383 0.00698 0.00137 -0.1218 0.5390 0.4906
2.000 0.7897 0.00607 0.00154 -0.1212 0.5257 1.0000
2.250 0.8172 0.00618 0.00161 -0.1213 0.5159 1.0000
2.500 0.8444 0.00633 0.00169 -0.1213 0.4992 1.0000
2.750 0.8714 0.00650 0.00177 -0.1213 0.4826 1.0000
3.000 0.8974 0.00678 0.00190 -0.1212 0.4510 1.0000
3.250 0.9230 0.00711 0.00206 -0.1210 0.4147 1.0000
3.500 0.9444 0.00793 0.00246 -0.1202 0.3328 1.0000
3.750 0.9545 0.01014 0.00362 -0.1179 0.1199 1.0000
4.000 0.9750 0.01108 0.00425 -0.1169 0.0231 1.0000
4.250 0.9992 0.01158 0.00484 -0.1163 0.0160 1.0000
4.500 1.0251 0.01182 0.00507 -0.1161 0.0144 1.0000
4.750 1.0496 0.01221 0.00553 -0.1156 0.0126 1.0000
5.000 1.0736 0.01266 0.00602 -0.1151 0.0112 1.0000
5.250 1.0933 0.01358 0.00705 -0.1137 0.0094 1.0000
5.500 1.1038 0.01534 0.00899 -0.1108 0.0087 1.0000
5.750 1.1305 0.01541 0.00906 -0.1108 0.0082 1.0000
6.000 1.1498 0.01615 0.00986 -0.1095 0.0077 1.0000
6.250 1.1665 0.01709 0.01086 -0.1078 0.0073 1.0000
6.500 1.1830 0.01798 0.01183 -0.1060 0.0067 1.0000
6.750 1.1996 0.01883 0.01272 -0.1044 0.0061 1.0000
7.000 1.2150 0.01975 0.01368 -0.1026 0.0056 1.0000
7.250 1.2261 0.02106 0.01503 -0.1000 0.0054 1.0000
7.750 1.2933 0.03386 0.02804 -0.0998 0.0087 1.0000
8.000 1.3113 0.03508 0.02944 -0.0982 0.0085 1.0000
8.250 1.3279 0.03293 0.02737 -0.0962 0.0072 1.0000
8.500 1.3478 0.03432 0.02892 -0.0949 0.0064 1.0000
8.750 1.3651 0.03603 0.03076 -0.0936 0.0059 1.0000
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Polar data table (+)
Polar graphs
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