GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 392 AIRFOIL (goe392-il) Reynolds number: 200,000 Max Cl/Cd: 77.55 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe392-il-200000-n5.txt Download as CSV file: xf-goe392-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2947 0.11297 0.10966 -0.0390 1.0000 0.0135
-9.250 -0.2942 0.11043 0.10717 -0.0384 1.0000 0.0144
-9.000 -0.2949 0.10797 0.10476 -0.0380 1.0000 0.0146
-8.750 -0.2941 0.10539 0.10222 -0.0381 0.9996 0.0149
-8.500 -0.2777 0.10097 0.09780 -0.0429 0.9962 0.0155
-8.250 -0.2622 0.09669 0.09353 -0.0475 0.9918 0.0163
-8.000 -0.2456 0.09249 0.08932 -0.0525 0.9874 0.0169
-7.750 -0.2315 0.08839 0.08523 -0.0570 0.9807 0.0177
-7.500 -0.2185 0.08441 0.08127 -0.0613 0.9727 0.0185
-7.250 -0.2066 0.08042 0.07727 -0.0663 0.9621 0.0198
-7.000 -0.1930 0.07635 0.07322 -0.0724 0.9489 0.0206
-6.750 -0.1722 0.07135 0.06821 -0.0810 0.9364 0.0210
-6.500 -0.1472 0.06577 0.06257 -0.0901 0.9259 0.0212
-6.250 -0.1187 0.05983 0.05653 -0.0990 0.9168 0.0213
-6.000 -0.0922 0.05428 0.05080 -0.1060 0.9059 0.0213
-5.750 -0.0656 0.04915 0.04543 -0.1118 0.8960 0.0214
-5.500 -0.0370 0.04436 0.04036 -0.1169 0.8870 0.0214
-5.250 -0.0152 0.03699 0.03281 -0.1198 0.8770 0.0109
-5.000 0.0111 0.03239 0.02783 -0.1230 0.8665 0.0103
-4.750 0.0395 0.02846 0.02343 -0.1250 0.8567 0.0099
-4.250 0.0974 0.02310 0.01708 -0.1265 0.8374 0.0109
-4.000 0.1257 0.02124 0.01470 -0.1266 0.8278 0.0117
-3.750 0.1534 0.01890 0.01187 -0.1267 0.8192 0.0119
-3.500 0.1794 0.01686 0.00944 -0.1262 0.8099 0.0123
-3.250 0.2059 0.01545 0.00779 -0.1259 0.8010 0.0132
-3.000 0.2331 0.01470 0.00686 -0.1257 0.7924 0.0161
-2.750 0.2585 0.01392 0.00592 -0.1251 0.7831 0.0188
-2.500 0.2847 0.01329 0.00514 -0.1246 0.7746 0.0217
-2.250 0.3099 0.01267 0.00439 -0.1243 0.7656 0.0293
-2.000 0.3355 0.01225 0.00380 -0.1239 0.7566 0.0401
-1.750 0.3617 0.01184 0.00331 -0.1236 0.7482 0.0649
-1.500 0.3837 0.01092 0.00325 -0.1231 0.7388 0.3449
-1.250 0.4094 0.01084 0.00314 -0.1227 0.7296 0.3972
-1.000 0.4344 0.01067 0.00304 -0.1222 0.7201 0.4515
-0.750 0.4586 0.01051 0.00293 -0.1215 0.7090 0.4925
-0.500 0.4813 0.01025 0.00290 -0.1205 0.6976 0.5744
-0.250 0.5022 0.00971 0.00293 -0.1187 0.6870 0.7937
0.250 0.5828 0.00963 0.00274 -0.1242 0.6656 1.0000
0.500 0.6079 0.00974 0.00273 -0.1238 0.6554 1.0000
0.750 0.6332 0.00985 0.00274 -0.1233 0.6458 1.0000
1.000 0.6584 0.00998 0.00276 -0.1229 0.6361 1.0000
1.250 0.6835 0.01010 0.00281 -0.1225 0.6260 1.0000
1.500 0.7086 0.01023 0.00289 -0.1220 0.6166 1.0000
2.000 0.7587 0.01052 0.00307 -0.1211 0.5974 1.0000
2.250 0.7836 0.01067 0.00320 -0.1207 0.5881 1.0000
2.500 0.8085 0.01084 0.00336 -0.1202 0.5792 1.0000
2.750 0.8335 0.01100 0.00354 -0.1198 0.5703 1.0000
3.000 0.8584 0.01118 0.00373 -0.1193 0.5620 1.0000
3.250 0.8825 0.01138 0.00392 -0.1187 0.5506 1.0000
3.500 0.8983 0.01172 0.00407 -0.1163 0.5040 1.0000
3.750 0.9153 0.01212 0.00429 -0.1142 0.4593 1.0000
4.000 0.9187 0.01326 0.00470 -0.1098 0.3400 1.0000
4.250 0.9048 0.01611 0.00615 -0.1031 0.0842 1.0000
4.500 0.9186 0.01710 0.00700 -0.1007 0.0196 1.0000
4.750 0.9364 0.01776 0.00789 -0.0988 0.0161 1.0000
5.000 0.9546 0.01834 0.00863 -0.0972 0.0141 1.0000
5.250 0.9707 0.01903 0.00950 -0.0951 0.0123 1.0000
5.500 0.9830 0.01987 0.01050 -0.0924 0.0115 1.0000
5.750 0.9907 0.02083 0.01161 -0.0889 0.0109 1.0000
6.000 0.9956 0.02196 0.01284 -0.0852 0.0106 1.0000
6.250 0.9978 0.02330 0.01424 -0.0813 0.0096 1.0000
6.500 0.9936 0.02519 0.01616 -0.0768 0.0087 1.0000
6.750 0.9979 0.02684 0.01790 -0.0735 0.0081 1.0000
7.000 1.0087 0.02823 0.01935 -0.0712 0.0080 1.0000
7.250 1.0240 0.02982 0.02097 -0.0694 0.0079 1.0000
7.500 1.0483 0.03156 0.02275 -0.0687 0.0079 1.0000
7.750 1.1112 0.03513 0.02632 -0.0736 0.0082 1.0000
8.000 1.1506 0.03709 0.02838 -0.0754 0.0089 1.0000
8.250 1.1673 0.03795 0.02954 -0.0727 0.0099 1.0000
8.750 1.2129 0.04382 0.03600 -0.0716 0.0072 1.0000
11.250 1.2201 0.07190 0.06665 -0.0428 0.0105 1.0000
11.500 1.2057 0.07537 0.07032 -0.0409 0.0105 1.0000
11.750 1.1911 0.07900 0.07414 -0.0396 0.0104 1.0000
12.000 1.1749 0.08300 0.07834 -0.0389 0.0104 1.0000
12.250 1.1577 0.08743 0.08293 -0.0388 0.0103 1.0000
12.500 1.1402 0.09210 0.08778 -0.0393 0.0103 1.0000
12.750 1.1225 0.09713 0.09298 -0.0405 0.0104 1.0000
13.000 1.1045 0.10255 0.09857 -0.0423 0.0104 1.0000
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Polar data table (+)
Polar graphs
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