GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Reynolds number: 500,000 Max Cl/Cd: 112.3 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe118-il-500000.txt Download as CSV file: xf-goe118-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2752 0.10388 0.10178 -0.0369 1.0000 0.0098
-8.750 -0.2701 0.10093 0.09886 -0.0380 1.0000 0.0104
-8.500 -0.2662 0.09814 0.09611 -0.0388 1.0000 0.0111
-8.250 -0.2604 0.09537 0.09335 -0.0405 0.9982 0.0119
-8.000 -0.2386 0.09171 0.08969 -0.0475 0.9870 0.0126
-7.750 -0.2180 0.08783 0.08581 -0.0534 0.9713 0.0128
-7.500 -0.2016 0.08390 0.08186 -0.0581 0.9492 0.0128
-7.250 -0.1893 0.08031 0.07822 -0.0615 0.9242 0.0129
-7.000 -0.1771 0.07676 0.07458 -0.0648 0.9008 0.0129
-6.750 -0.1629 0.07306 0.07079 -0.0687 0.8796 0.0129
-6.500 -0.1462 0.06918 0.06681 -0.0731 0.8615 0.0129
-6.250 -0.1332 0.06219 0.05975 -0.0800 0.8456 0.0134
-6.000 -0.1151 0.05747 0.05493 -0.0851 0.8313 0.0139
-5.250 -0.0435 0.04665 0.04377 -0.0980 0.7951 0.0156
-5.000 -0.0143 0.04255 0.03951 -0.1030 0.7852 0.0164
-4.750 0.0170 0.03813 0.03490 -0.1078 0.7763 0.0175
-4.500 0.0496 0.03341 0.02993 -0.1121 0.7677 0.0190
-4.250 0.0839 0.03002 0.02628 -0.1142 0.7595 0.0220
-4.000 0.1154 0.02577 0.02156 -0.1165 0.7523 0.0224
-3.250 0.2028 0.01362 0.00766 -0.1197 0.7306 0.0178
-3.000 0.2309 0.01297 0.00679 -0.1197 0.7236 0.0203
-2.750 0.2596 0.01181 0.00540 -0.1197 0.7160 0.0195
-2.500 0.2879 0.01098 0.00436 -0.1196 0.7092 0.0192
-2.250 0.3163 0.01036 0.00359 -0.1196 0.7017 0.0201
-2.000 0.3445 0.00998 0.00309 -0.1196 0.6946 0.0219
-1.750 0.3728 0.00955 0.00252 -0.1196 0.6866 0.0265
-1.500 0.4011 0.00928 0.00211 -0.1196 0.6787 0.0332
-1.250 0.4289 0.00915 0.00211 -0.1196 0.6710 0.0937
-1.000 0.4569 0.00925 0.00219 -0.1198 0.6632 0.1079
-0.500 0.5126 0.00928 0.00214 -0.1200 0.6492 0.1224
0.000 0.5684 0.00917 0.00198 -0.1202 0.6357 0.1327
0.500 0.6241 0.00907 0.00187 -0.1205 0.6217 0.1460
0.750 0.6517 0.00902 0.00183 -0.1205 0.6138 0.1627
1.000 0.6790 0.00844 0.00193 -0.1210 0.6052 0.4261
1.250 0.7025 0.00726 0.00199 -0.1202 0.5975 1.0000
1.500 0.7300 0.00737 0.00201 -0.1202 0.5898 1.0000
1.750 0.7577 0.00745 0.00206 -0.1202 0.5818 1.0000
2.000 0.7850 0.00758 0.00211 -0.1202 0.5747 1.0000
2.250 0.8126 0.00766 0.00220 -0.1203 0.5671 1.0000
2.500 0.8399 0.00779 0.00229 -0.1203 0.5602 1.0000
2.750 0.8667 0.00791 0.00236 -0.1203 0.5480 1.0000
3.000 0.8934 0.00804 0.00245 -0.1202 0.5332 1.0000
3.250 0.9197 0.00819 0.00254 -0.1200 0.5122 1.0000
3.500 0.9452 0.00842 0.00269 -0.1197 0.4852 1.0000
3.750 0.9694 0.00878 0.00287 -0.1193 0.4438 1.0000
4.000 0.9817 0.01048 0.00360 -0.1172 0.2785 1.0000
4.250 0.9867 0.01320 0.00520 -0.1140 0.0286 1.0000
4.500 1.0111 0.01361 0.00572 -0.1135 0.0240 1.0000
4.750 1.0342 0.01416 0.00639 -0.1127 0.0205 1.0000
5.000 1.0540 0.01506 0.00743 -0.1114 0.0172 1.0000
5.250 1.0688 0.01639 0.00891 -0.1093 0.0159 1.0000
5.500 1.0888 0.01711 0.00971 -0.1080 0.0151 1.0000
5.750 1.1042 0.01820 0.01089 -0.1060 0.0147 1.0000
6.000 1.1162 0.01951 0.01228 -0.1035 0.0147 1.0000
6.250 1.1315 0.02050 0.01333 -0.1015 0.0138 1.0000
6.500 1.1459 0.02153 0.01441 -0.0995 0.0127 1.0000
6.750 1.1574 0.02292 0.01589 -0.0969 0.0123 1.0000
7.000 1.1711 0.02458 0.01760 -0.0944 0.0124 1.0000
7.750 1.2833 0.03787 0.03098 -0.0975 0.0159 1.0000
8.000 1.3021 0.03988 0.03321 -0.0960 0.0158 1.0000
8.250 1.3162 0.03993 0.03349 -0.0936 0.0154 1.0000
8.500 1.3319 0.03944 0.03319 -0.0913 0.0139 1.0000
8.750 1.3482 0.04080 0.03477 -0.0894 0.0123 1.0000
9.000 1.3617 0.04276 0.03689 -0.0878 0.0110 1.0000
9.250 1.3747 0.04528 0.03953 -0.0863 0.0103 1.0000
9.500 1.3887 0.04844 0.04279 -0.0852 0.0098 1.0000
9.750 1.3969 0.05354 0.04805 -0.0837 0.0093 1.0000
10.000 1.3814 0.06403 0.05901 -0.0798 0.0087 1.0000
10.250 1.3763 0.06715 0.06239 -0.0763 0.0087 1.0000
10.500 1.3684 0.07019 0.06565 -0.0727 0.0087 1.0000
10.750 1.3561 0.07301 0.06869 -0.0689 0.0087 1.0000
11.000 1.3396 0.07557 0.07143 -0.0647 0.0087 1.0000
11.250 1.3214 0.07834 0.07436 -0.0611 0.0087 1.0000
11.500 1.3026 0.08143 0.07761 -0.0585 0.0087 1.0000
11.750 1.2838 0.08488 0.08123 -0.0566 0.0087 1.0000
12.000 1.2645 0.08869 0.08520 -0.0556 0.0086 1.0000
12.250 1.2452 0.09287 0.08952 -0.0552 0.0086 1.0000
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Polar data table (+)
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