GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 342 AIRFOIL (goe342-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.77 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe342-il-1000000.txt Download as CSV file: xf-goe342-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 342 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2101 0.08558 0.08397 -0.0513 0.9709 0.0128
-7.250 -0.1938 0.08209 0.08046 -0.0556 0.9566 0.0128
-7.000 -0.1855 0.07864 0.07698 -0.0553 0.9427 0.0130
-6.750 -0.1719 0.07622 0.07452 -0.0569 0.9274 0.0132
-6.500 -0.1556 0.07372 0.07195 -0.0595 0.9119 0.0136
-6.250 -0.1370 0.07093 0.06910 -0.0629 0.8968 0.0142
-6.000 -0.1144 0.06768 0.06577 -0.0675 0.8821 0.0155
-5.750 -0.0757 0.06313 0.06112 -0.0785 0.8677 0.0159
-5.500 -0.0428 0.05896 0.05685 -0.0863 0.8555 0.0160
-5.250 -0.0216 0.05472 0.05254 -0.0896 0.8447 0.0162
-5.000 -0.0020 0.05250 0.05027 -0.0910 0.8341 0.0164
-4.750 0.0241 0.05017 0.04786 -0.0942 0.8239 0.0169
-4.500 0.0551 0.04738 0.04501 -0.0987 0.8155 0.0179
-4.250 0.1091 0.04311 0.04054 -0.1088 0.8085 0.0195
-4.000 0.1475 0.03948 0.03679 -0.1142 0.8020 0.0196
-3.750 0.1804 0.03487 0.03205 -0.1190 0.7956 0.0200
-3.500 0.2067 0.03308 0.03019 -0.1207 0.7896 0.0203
-3.250 0.2365 0.03122 0.02826 -0.1229 0.7834 0.0208
-3.000 0.2688 0.02921 0.02613 -0.1253 0.7779 0.0216
-2.750 0.3101 0.02683 0.02356 -0.1283 0.7734 0.0238
-2.500 0.3475 0.02436 0.02088 -0.1306 0.7685 0.0240
-2.250 0.3817 0.02194 0.01821 -0.1324 0.7629 0.0241
0.000 0.6553 0.01063 0.00555 -0.1399 0.7122 0.0326
0.250 0.6839 0.01024 0.00506 -0.1400 0.7032 0.0340
0.500 0.7123 0.01034 0.00509 -0.1398 0.6955 0.0365
0.750 0.7418 0.00952 0.00408 -0.1401 0.6878 0.0382
1.000 0.7705 0.00898 0.00356 -0.1404 0.6781 0.0397
1.250 0.7987 0.00870 0.00325 -0.1404 0.6653 0.0416
1.500 0.8266 0.00857 0.00306 -0.1403 0.6471 0.0444
1.750 0.8542 0.00825 0.00265 -0.1404 0.6159 0.0515
2.000 0.8795 0.00843 0.00234 -0.1395 0.5294 0.0350
2.250 0.9037 0.00888 0.00241 -0.1390 0.4505 0.0348
2.500 0.9294 0.00915 0.00247 -0.1387 0.4036 0.0351
2.750 0.9560 0.00931 0.00252 -0.1385 0.3770 0.0357
3.000 0.9828 0.00943 0.00254 -0.1384 0.3574 0.0355
3.250 1.0097 0.00954 0.00259 -0.1382 0.3422 0.0359
3.500 1.0367 0.00965 0.00266 -0.1381 0.3312 0.0369
3.750 1.0639 0.00972 0.00270 -0.1380 0.3224 0.0394
4.250 1.1176 0.00996 0.00291 -0.1377 0.3059 0.0462
4.500 1.1418 0.00882 0.00333 -0.1375 0.2989 1.0000
4.750 1.1686 0.00896 0.00347 -0.1373 0.2920 1.0000
5.000 1.1948 0.00918 0.00364 -0.1370 0.2829 1.0000
5.250 1.2214 0.00934 0.00379 -0.1368 0.2737 1.0000
5.500 1.2471 0.00959 0.00397 -0.1365 0.2573 1.0000
5.750 1.2724 0.00989 0.00418 -0.1361 0.2365 1.0000
6.000 1.2944 0.01056 0.00455 -0.1353 0.1822 1.0000
6.250 1.3135 0.01159 0.00522 -0.1340 0.1213 1.0000
6.500 1.3373 0.01204 0.00560 -0.1334 0.1075 1.0000
6.750 1.3614 0.01242 0.00595 -0.1329 0.0968 1.0000
7.000 1.3852 0.01283 0.00631 -0.1323 0.0848 1.0000
7.250 1.4085 0.01327 0.00667 -0.1316 0.0713 1.0000
7.500 1.4317 0.01373 0.00706 -0.1309 0.0608 1.0000
7.750 1.4548 0.01416 0.00748 -0.1302 0.0539 1.0000
8.000 1.4780 0.01456 0.00787 -0.1296 0.0473 1.0000
8.250 1.4997 0.01512 0.00837 -0.1287 0.0359 1.0000
8.500 1.5183 0.01600 0.00909 -0.1273 0.0203 1.0000
8.750 1.5389 0.01663 0.00973 -0.1262 0.0166 1.0000
9.000 1.5584 0.01735 0.01048 -0.1248 0.0144 1.0000
9.250 1.5783 0.01798 0.01118 -0.1236 0.0134 1.0000
9.500 1.5981 0.01857 0.01183 -0.1224 0.0127 1.0000
9.750 1.6169 0.01923 0.01254 -0.1210 0.0119 1.0000
10.000 1.6337 0.02003 0.01341 -0.1194 0.0111 1.0000
10.250 1.6439 0.02136 0.01486 -0.1166 0.0102 1.0000
10.500 1.6615 0.02192 0.01547 -0.1151 0.0100 1.0000
10.750 1.6764 0.02261 0.01624 -0.1132 0.0096 1.0000
11.000 1.6873 0.02341 0.01711 -0.1105 0.0092 1.0000
11.250 1.6971 0.02429 0.01806 -0.1078 0.0089 1.0000
11.500 1.7062 0.02526 0.01912 -0.1052 0.0086 1.0000
11.750 1.7145 0.02633 0.02026 -0.1026 0.0083 1.0000
12.000 1.7204 0.02761 0.02163 -0.0998 0.0080 1.0000
12.250 1.7212 0.02936 0.02348 -0.0967 0.0077 1.0000
12.500 1.7146 0.03183 0.02610 -0.0930 0.0075 1.0000
12.750 1.7114 0.03416 0.02857 -0.0901 0.0073 1.0000
13.000 1.7176 0.03575 0.03026 -0.0883 0.0072 1.0000
13.250 1.7215 0.03759 0.03221 -0.0865 0.0071 1.0000
13.500 1.7243 0.03963 0.03435 -0.0848 0.0070 1.0000
13.750 1.7255 0.04191 0.03675 -0.0832 0.0069 1.0000
14.000 1.7261 0.04430 0.03926 -0.0818 0.0067 1.0000
14.250 1.7253 0.04694 0.04201 -0.0806 0.0066 1.0000
14.500 1.7248 0.04964 0.04482 -0.0796 0.0064 1.0000
14.750 1.7223 0.05264 0.04793 -0.0787 0.0063 1.0000
15.000 1.7190 0.05581 0.05121 -0.0780 0.0062 1.0000
15.250 1.7145 0.05929 0.05481 -0.0775 0.0060 1.0000
15.500 1.7085 0.06312 0.05876 -0.0774 0.0059 1.0000
15.750 1.7011 0.06730 0.06306 -0.0775 0.0059 1.0000
16.000 1.6916 0.07201 0.06790 -0.0781 0.0058 1.0000
16.250 1.6814 0.07710 0.07311 -0.0791 0.0057 1.0000
16.500 1.6698 0.08261 0.07875 -0.0805 0.0057 1.0000
16.750 1.6574 0.08848 0.08475 -0.0823 0.0056 1.0000
17.000 1.6434 0.09483 0.09123 -0.0845 0.0056 1.0000
17.250 1.6288 0.10142 0.09795 -0.0869 0.0055 1.0000
17.500 1.6136 0.10819 0.10485 -0.0896 0.0055 1.0000
17.750 1.5981 0.11510 0.11189 -0.0925 0.0055 1.0000
18.000 1.5825 0.12214 0.11905 -0.0956 0.0054 1.0000
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Polar data table (+)
Polar graphs
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