GOE 370 AIRFOIL (goe370-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 370 AIRFOIL (goe370-il) Reynolds number: 1,000,000 Max Cl/Cd: 154.2 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe370-il-1000000.txt Download as CSV file: xf-goe370-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 370 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3169 0.10036 0.09879 -0.0263 1.0000 0.0077
-8.250 -0.3140 0.09786 0.09630 -0.0263 1.0000 0.0082
-8.000 -0.3130 0.09560 0.09406 -0.0259 1.0000 0.0082
-7.750 -0.3079 0.09315 0.09164 -0.0271 0.9995 0.0084
-7.500 -0.2873 0.08913 0.08762 -0.0330 0.9965 0.0085
-7.250 -0.2685 0.08526 0.08375 -0.0382 0.9909 0.0085
-7.000 -0.2441 0.08079 0.07928 -0.0451 0.9850 0.0086
-6.750 -0.2220 0.07664 0.07512 -0.0509 0.9765 0.0086
-6.250 -0.1614 0.06478 0.06321 -0.0691 0.9590 0.0089
-6.000 -0.1260 0.06105 0.05943 -0.0763 0.9487 0.0095
-5.750 -0.0856 0.05740 0.05570 -0.0846 0.9313 0.0109
-5.500 -0.0458 0.05361 0.05172 -0.0928 0.9014 0.0131
-5.250 -0.0235 0.05029 0.04824 -0.0960 0.8750 0.0132
-4.500 0.0462 0.01360 0.00979 -0.1146 0.8283 0.0102
-4.250 0.0717 0.01277 0.00873 -0.1143 0.8195 0.0112
-4.000 0.0971 0.01153 0.00718 -0.1140 0.8116 0.0123
-3.750 0.1231 0.01088 0.00630 -0.1136 0.8044 0.0131
-3.500 0.1482 0.00946 0.00454 -0.1131 0.7975 0.0149
-3.000 0.2029 0.00989 0.00498 -0.1128 0.7846 0.0185
-2.750 0.2301 0.00996 0.00498 -0.1125 0.7787 0.0197
-2.500 0.2556 0.00873 0.00351 -0.1122 0.7735 0.0227
-2.250 0.2827 0.00869 0.00345 -0.1120 0.7679 0.0252
-2.000 0.3095 0.00852 0.00319 -0.1117 0.7628 0.0275
-1.750 0.3366 0.00834 0.00297 -0.1115 0.7574 0.0292
-1.500 0.3639 0.00847 0.00306 -0.1113 0.7518 0.0301
-1.250 0.3898 0.00770 0.00215 -0.1109 0.7468 0.0319
-1.000 0.4164 0.00740 0.00179 -0.1106 0.7414 0.0325
-0.750 0.4430 0.00719 0.00151 -0.1103 0.7362 0.0331
-0.500 0.4697 0.00700 0.00129 -0.1100 0.7298 0.0346
-0.250 0.4961 0.00688 0.00110 -0.1095 0.7220 0.0361
0.000 0.5227 0.00675 0.00096 -0.1092 0.7129 0.0396
0.250 0.5492 0.00670 0.00086 -0.1089 0.7039 0.0425
0.500 0.5755 0.00665 0.00080 -0.1085 0.6943 0.0542
0.750 0.6019 0.00653 0.00081 -0.1082 0.6847 0.1016
1.000 0.6285 0.00652 0.00085 -0.1079 0.6757 0.1283
1.250 0.6550 0.00654 0.00087 -0.1076 0.6662 0.1398
1.500 0.6817 0.00656 0.00089 -0.1074 0.6550 0.1499
1.750 0.7081 0.00657 0.00092 -0.1071 0.6432 0.1619
2.000 0.7343 0.00658 0.00096 -0.1068 0.6300 0.1740
2.250 0.7603 0.00660 0.00100 -0.1064 0.6152 0.1946
2.500 0.7851 0.00651 0.00114 -0.1059 0.5990 0.3314
2.750 0.8327 0.00540 0.00134 -0.1110 0.5809 1.0000
3.000 0.8560 0.00563 0.00146 -0.1100 0.5533 1.0000
3.250 0.8788 0.00592 0.00159 -0.1090 0.5209 1.0000
3.500 0.9029 0.00612 0.00172 -0.1083 0.5022 1.0000
3.750 0.9265 0.00636 0.00186 -0.1074 0.4740 1.0000
4.000 0.9479 0.00679 0.00204 -0.1062 0.4132 1.0000
4.250 0.9609 0.00797 0.00256 -0.1037 0.2789 1.0000
4.500 0.9640 0.01022 0.00364 -0.0996 0.0416 1.0000
4.750 0.9858 0.01073 0.00410 -0.0985 0.0194 1.0000
5.000 1.0087 0.01111 0.00449 -0.0975 0.0156 1.0000
5.250 1.0295 0.01174 0.00523 -0.0961 0.0127 1.0000
5.500 1.0525 0.01210 0.00563 -0.0952 0.0119 1.0000
5.750 1.0744 0.01257 0.00617 -0.0941 0.0110 1.0000
6.000 1.0958 0.01308 0.00672 -0.0929 0.0099 1.0000
6.250 1.1161 0.01368 0.00737 -0.0915 0.0091 1.0000
6.500 1.1301 0.01489 0.00867 -0.0890 0.0080 1.0000
6.750 1.1398 0.01658 0.01049 -0.0858 0.0075 1.0000
7.000 1.1598 0.01721 0.01117 -0.0845 0.0073 1.0000
7.250 1.1784 0.01804 0.01207 -0.0829 0.0070 1.0000
7.500 1.1964 0.01905 0.01317 -0.0812 0.0067 1.0000
7.750 1.2150 0.02006 0.01426 -0.0797 0.0062 1.0000
8.000 1.2338 0.02119 0.01546 -0.0782 0.0057 1.0000
8.250 1.2527 0.02266 0.01702 -0.0768 0.0054 1.0000
16.250 0.8722 0.19622 0.19496 -0.1027 0.0061 1.0000
16.500 0.8734 0.20065 0.19939 -0.1048 0.0062 1.0000
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Polar data table (+)
Polar graphs
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