GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 392 AIRFOIL (goe392-il) Reynolds number: 500,000 Max Cl/Cd: 105.31 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe392-il-500000.txt Download as CSV file: xf-goe392-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2207 0.07260 0.07062 -0.0699 0.9752 0.0128
-7.000 -0.1952 0.06788 0.06589 -0.0776 0.9710 0.0135
-6.750 -0.1755 0.06290 0.06087 -0.0850 0.9618 0.0139
-6.500 -0.1450 0.05681 0.05473 -0.0957 0.9572 0.0144
-6.250 -0.1201 0.05098 0.04882 -0.1039 0.9461 0.0150
-6.000 -0.0888 0.04440 0.04207 -0.1129 0.9357 0.0157
-5.750 -0.0547 0.03856 0.03597 -0.1200 0.9260 0.0168
-5.500 -0.0139 0.03575 0.03279 -0.1242 0.9162 0.0187
-5.250 0.0170 0.03264 0.02930 -0.1271 0.9025 0.0189
-5.000 0.0442 0.02963 0.02592 -0.1289 0.8874 0.0190
-4.750 0.0691 0.02678 0.02267 -0.1295 0.8721 0.0191
-4.500 0.0844 0.02059 0.01593 -0.1295 0.8577 0.0205
-4.250 0.1080 0.01853 0.01360 -0.1293 0.8451 0.0215
-3.750 0.1579 0.01532 0.00977 -0.1280 0.8235 0.0231
-3.500 0.1842 0.01387 0.00791 -0.1267 0.8133 0.0203
-3.250 0.2107 0.01336 0.00722 -0.1261 0.8037 0.0194
-3.000 0.2352 0.01176 0.00544 -0.1253 0.7950 0.0199
-2.750 0.2584 0.01065 0.00426 -0.1244 0.7853 0.0224
-2.500 0.2835 0.01025 0.00378 -0.1239 0.7757 0.0256
-2.250 0.3086 0.00990 0.00332 -0.1232 0.7656 0.0289
-1.750 0.3576 0.00909 0.00227 -0.1218 0.7438 0.0400
-1.500 0.3833 0.00892 0.00199 -0.1214 0.7338 0.0458
-1.250 0.4056 0.00811 0.00176 -0.1207 0.7246 0.2604
-1.000 0.4300 0.00788 0.00181 -0.1202 0.7150 0.3918
-0.750 0.4554 0.00781 0.00177 -0.1197 0.7048 0.4282
-0.500 0.4807 0.00773 0.00174 -0.1193 0.6951 0.4574
-0.250 0.5045 0.00752 0.00172 -0.1186 0.6855 0.5294
0.000 0.5224 0.00698 0.00181 -0.1166 0.6754 0.7496
0.250 0.5857 0.00662 0.00182 -0.1244 0.6640 1.0000
0.500 0.6103 0.00671 0.00182 -0.1238 0.6536 1.0000
0.750 0.6349 0.00681 0.00184 -0.1232 0.6436 1.0000
1.000 0.6596 0.00692 0.00186 -0.1226 0.6332 1.0000
1.250 0.6844 0.00702 0.00190 -0.1221 0.6227 1.0000
1.500 0.7092 0.00713 0.00195 -0.1215 0.6125 1.0000
1.750 0.7339 0.00726 0.00201 -0.1210 0.6026 1.0000
2.000 0.7588 0.00738 0.00211 -0.1205 0.5929 1.0000
2.250 0.7839 0.00750 0.00220 -0.1200 0.5836 1.0000
2.500 0.8067 0.00766 0.00227 -0.1190 0.5657 1.0000
2.750 0.8274 0.00790 0.00235 -0.1176 0.5366 1.0000
3.000 0.8504 0.00808 0.00247 -0.1167 0.5159 1.0000
3.250 0.8717 0.00834 0.00263 -0.1155 0.4864 1.0000
3.500 0.8854 0.00899 0.00285 -0.1129 0.4039 1.0000
3.750 0.8877 0.01063 0.00355 -0.1085 0.2429 1.0000
4.000 0.8862 0.01272 0.00473 -0.1035 0.0253 1.0000
4.250 0.9085 0.01306 0.00516 -0.1024 0.0218 1.0000
4.500 0.9297 0.01347 0.00566 -0.1012 0.0195 1.0000
4.750 0.9487 0.01403 0.00636 -0.0995 0.0168 1.0000
5.000 0.9636 0.01486 0.00732 -0.0971 0.0157 1.0000
5.250 0.9720 0.01601 0.00861 -0.0935 0.0151 1.0000
5.500 0.9844 0.01679 0.00946 -0.0907 0.0149 1.0000
5.750 0.9875 0.01793 0.01067 -0.0861 0.0153 1.0000
6.000 1.0011 0.01854 0.01132 -0.0835 0.0158 1.0000
6.250 1.0009 0.02014 0.01298 -0.0788 0.0149 1.0000
6.500 1.0110 0.02201 0.01485 -0.0759 0.0151 1.0000
6.750 1.0293 0.02228 0.01518 -0.0742 0.0158 1.0000
10.250 1.3050 0.06270 0.05762 -0.0635 0.0081 1.0000
10.500 1.2983 0.06545 0.06060 -0.0596 0.0081 1.0000
10.750 1.2874 0.06801 0.06337 -0.0554 0.0081 1.0000
11.000 1.2739 0.07030 0.06584 -0.0508 0.0081 1.0000
11.250 1.2564 0.07263 0.06834 -0.0463 0.0081 1.0000
11.500 1.2396 0.07521 0.07108 -0.0427 0.0081 1.0000
11.750 1.2198 0.07804 0.07408 -0.0397 0.0081 1.0000
12.000 1.2018 0.08120 0.07740 -0.0376 0.0081 1.0000
12.250 1.1829 0.08471 0.08106 -0.0363 0.0081 1.0000
12.500 1.1658 0.08861 0.08509 -0.0358 0.0081 1.0000
12.750 1.1462 0.09281 0.08945 -0.0358 0.0081 1.0000
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Polar data table (+)
Polar graphs
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