GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 392 AIRFOIL (goe392-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.76 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe392-il-1000000.txt Download as CSV file: xf-goe392-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 392 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2509 0.09301 0.09148 -0.0546 0.9933 0.0067
-8.500 -0.2385 0.08837 0.08685 -0.0588 0.9906 0.0068
-8.250 -0.2239 0.08418 0.08266 -0.0633 0.9879 0.0068
-8.000 -0.2084 0.07918 0.07767 -0.0691 0.9852 0.0068
-7.750 -0.1923 0.07442 0.07291 -0.0749 0.9821 0.0068
-7.500 -0.1929 0.06750 0.06603 -0.0813 0.9729 0.0072
-7.250 -0.1765 0.06303 0.06155 -0.0877 0.9656 0.0074
-7.000 -0.1535 0.05844 0.05693 -0.0955 0.9582 0.0076
-6.750 -0.1261 0.05380 0.05223 -0.1040 0.9472 0.0082
-6.500 -0.0858 0.04689 0.04520 -0.1172 0.9356 0.0088
-6.250 -0.0475 0.03932 0.03738 -0.1287 0.9150 0.0094
-6.000 -0.0222 0.03438 0.03210 -0.1329 0.8839 0.0101
-5.750 0.0002 0.03187 0.02927 -0.1331 0.8573 0.0110
-5.500 0.0195 0.02988 0.02699 -0.1326 0.8382 0.0113
-4.500 0.0817 0.01404 0.00933 -0.1274 0.7915 0.0081
-4.250 0.1053 0.01274 0.00777 -0.1265 0.7827 0.0086
-4.000 0.1305 0.01205 0.00694 -0.1260 0.7741 0.0098
-3.750 0.1554 0.01121 0.00592 -0.1253 0.7659 0.0105
-3.500 0.1808 0.01072 0.00531 -0.1248 0.7571 0.0111
-3.250 0.2056 0.01004 0.00450 -0.1242 0.7476 0.0118
-3.000 0.2271 0.00873 0.00303 -0.1229 0.7374 0.0131
-2.750 0.2526 0.00857 0.00281 -0.1224 0.7264 0.0153
-2.500 0.2780 0.00830 0.00246 -0.1220 0.7161 0.0170
-2.250 0.3047 0.00827 0.00238 -0.1217 0.7069 0.0188
-2.000 0.3292 0.00779 0.00177 -0.1211 0.6979 0.0238
-1.750 0.3552 0.00767 0.00158 -0.1208 0.6882 0.0283
-1.500 0.3817 0.00762 0.00149 -0.1205 0.6787 0.0304
-1.250 0.4075 0.00748 0.00123 -0.1201 0.6691 0.0372
-0.750 0.4549 0.00660 0.00108 -0.1190 0.6482 0.3379
-0.500 0.4808 0.00657 0.00110 -0.1188 0.6378 0.3792
0.000 0.5327 0.00660 0.00110 -0.1182 0.6169 0.4186
0.250 0.5584 0.00660 0.00111 -0.1179 0.6059 0.4435
0.500 0.5836 0.00652 0.00113 -0.1175 0.5953 0.4904
0.750 0.6056 0.00619 0.00123 -0.1165 0.5857 0.6664
1.000 0.6217 0.00571 0.00134 -0.1139 0.5768 0.8880
1.250 0.6886 0.00572 0.00142 -0.1230 0.5656 1.0000
1.500 0.7138 0.00581 0.00147 -0.1226 0.5571 1.0000
1.750 0.7386 0.00593 0.00153 -0.1221 0.5486 1.0000
2.000 0.7629 0.00607 0.00160 -0.1214 0.5329 1.0000
2.250 0.7860 0.00626 0.00168 -0.1206 0.5103 1.0000
2.500 0.8099 0.00644 0.00177 -0.1199 0.4905 1.0000
2.750 0.8331 0.00665 0.00188 -0.1191 0.4671 1.0000
3.000 0.8528 0.00708 0.00204 -0.1176 0.4133 1.0000
3.250 0.8608 0.00832 0.00257 -0.1141 0.2793 1.0000
3.500 0.8558 0.01058 0.00373 -0.1082 0.0207 1.0000
3.750 0.8796 0.01082 0.00402 -0.1074 0.0160 1.0000
4.000 0.9027 0.01109 0.00436 -0.1066 0.0145 1.0000
4.250 0.9253 0.01139 0.00469 -0.1057 0.0129 1.0000
4.500 0.9471 0.01175 0.00509 -0.1046 0.0118 1.0000
4.750 0.9680 0.01216 0.00557 -0.1033 0.0106 1.0000
5.000 0.9863 0.01275 0.00622 -0.1015 0.0096 1.0000
5.250 1.0011 0.01353 0.00709 -0.0990 0.0091 1.0000
5.500 1.0088 0.01464 0.00831 -0.0953 0.0086 1.0000
5.750 1.0059 0.01616 0.00992 -0.0895 0.0082 1.0000
6.000 1.0299 0.01619 0.00998 -0.0889 0.0077 1.0000
6.250 1.0422 0.01681 0.01065 -0.0861 0.0073 1.0000
6.500 1.0535 0.01754 0.01144 -0.0831 0.0068 1.0000
6.750 1.0626 0.01850 0.01245 -0.0798 0.0064 1.0000
7.000 1.0720 0.01983 0.01383 -0.0766 0.0062 1.0000
7.250 1.1603 0.02795 0.02181 -0.0880 0.0081 1.0000
7.500 1.1862 0.03003 0.02401 -0.0876 0.0081 1.0000
7.750 1.2083 0.03195 0.02606 -0.0866 0.0080 1.0000
8.000 1.2265 0.03356 0.02783 -0.0849 0.0080 1.0000
8.250 1.2376 0.03280 0.02723 -0.0818 0.0075 1.0000
8.500 1.2529 0.03265 0.02719 -0.0795 0.0065 1.0000
8.750 1.2704 0.03404 0.02870 -0.0779 0.0058 1.0000
9.000 1.2863 0.03581 0.03060 -0.0763 0.0055 1.0000
9.250 1.2991 0.03763 0.03255 -0.0744 0.0052 1.0000
9.500 1.3108 0.03970 0.03474 -0.0725 0.0050 1.0000
9.750 1.3226 0.04201 0.03714 -0.0709 0.0048 1.0000
10.500 1.3008 0.05675 0.05272 -0.0586 0.0043 1.0000
10.750 1.2860 0.05896 0.05511 -0.0531 0.0043 1.0000
11.000 1.2728 0.06124 0.05754 -0.0486 0.0043 1.0000
11.250 1.2563 0.06380 0.06027 -0.0444 0.0043 1.0000
11.500 1.2407 0.06655 0.06317 -0.0410 0.0043 1.0000
11.750 1.2222 0.06967 0.06646 -0.0382 0.0043 1.0000
12.000 1.2052 0.07301 0.06993 -0.0363 0.0043 1.0000
12.250 1.1871 0.07671 0.07378 -0.0350 0.0043 1.0000
12.500 1.1701 0.08068 0.07787 -0.0345 0.0043 1.0000
12.750 1.1510 0.08512 0.08245 -0.0346 0.0043 1.0000
13.000 1.1315 0.08994 0.08741 -0.0353 0.0043 1.0000
13.250 1.1144 0.09494 0.09253 -0.0367 0.0043 1.0000
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Polar data table (+)
Polar graphs
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