GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 456 AIRFOIL (goe456-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.94 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe456-il-1000000.txt Download as CSV file: xf-goe456-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 456 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3163 0.11113 0.10952 -0.0321 1.0000 0.0055
-9.500 -0.3143 0.10859 0.10700 -0.0320 1.0000 0.0055
-9.250 -0.3142 0.10607 0.10451 -0.0315 1.0000 0.0058
-9.000 -0.3100 0.10318 0.10164 -0.0323 0.9997 0.0059
-8.750 -0.2949 0.09904 0.09750 -0.0363 0.9985 0.0067
-8.500 -0.2778 0.09474 0.09321 -0.0418 0.9964 0.0072
-8.250 -0.2627 0.09087 0.08933 -0.0459 0.9936 0.0073
-8.000 -0.2481 0.08706 0.08552 -0.0498 0.9900 0.0073
-7.750 -0.2318 0.08278 0.08125 -0.0547 0.9859 0.0073
-7.500 -0.2145 0.07825 0.07672 -0.0602 0.9816 0.0074
-7.250 -0.1995 0.07433 0.07281 -0.0648 0.9737 0.0074
-7.000 -0.1772 0.06617 0.06465 -0.0767 0.9695 0.0079
-6.750 -0.1527 0.06282 0.06127 -0.0824 0.9620 0.0083
-6.500 -0.1207 0.05845 0.05686 -0.0910 0.9563 0.0087
-6.250 -0.0929 0.05438 0.05273 -0.0980 0.9448 0.0094
-6.000 -0.0675 0.05006 0.04832 -0.1044 0.9316 0.0102
-5.750 -0.0435 0.04562 0.04378 -0.1097 0.9183 0.0112
-5.500 -0.0176 0.04210 0.04015 -0.1131 0.9069 0.0120
-5.250 0.0062 0.03752 0.03544 -0.1168 0.8962 0.0121
-5.000 0.0310 0.03119 0.02888 -0.1205 0.8865 0.0122
-4.750 0.0536 0.02650 0.02384 -0.1225 0.8771 0.0122
-4.500 0.0760 0.02305 0.02004 -0.1233 0.8689 0.0122
-4.250 0.0990 0.02017 0.01678 -0.1234 0.8614 0.0122
-4.000 0.1151 0.01103 0.00645 -0.1222 0.8533 0.0085
-3.750 0.1415 0.01049 0.00577 -0.1219 0.8464 0.0094
-3.500 0.1679 0.00987 0.00504 -0.1215 0.8388 0.0104
-3.250 0.1943 0.00927 0.00430 -0.1211 0.8315 0.0110
-3.000 0.2211 0.00888 0.00380 -0.1208 0.8236 0.0118
-2.750 0.2478 0.00852 0.00334 -0.1205 0.8161 0.0125
-2.500 0.2733 0.00754 0.00216 -0.1198 0.8079 0.0143
-2.250 0.3002 0.00727 0.00183 -0.1196 0.7991 0.0168
-2.000 0.3271 0.00710 0.00157 -0.1192 0.7900 0.0192
-1.750 0.3537 0.00686 0.00125 -0.1189 0.7801 0.0269
-1.500 0.3797 0.00643 0.00105 -0.1186 0.7697 0.1146
-1.250 0.4064 0.00638 0.00102 -0.1183 0.7583 0.1412
-1.000 0.4330 0.00637 0.00098 -0.1180 0.7446 0.1562
-0.750 0.4592 0.00639 0.00092 -0.1176 0.7270 0.1663
-0.500 0.4850 0.00641 0.00090 -0.1172 0.7071 0.1830
-0.250 0.5108 0.00644 0.00088 -0.1168 0.6868 0.1964
0.000 0.5365 0.00647 0.00088 -0.1164 0.6696 0.2184
0.250 0.5626 0.00647 0.00090 -0.1160 0.6546 0.2518
0.500 0.5886 0.00646 0.00093 -0.1157 0.6408 0.2954
0.750 0.6144 0.00644 0.00098 -0.1154 0.6275 0.3488
1.000 0.6388 0.00615 0.00107 -0.1149 0.6148 0.5288
1.500 0.7029 0.00538 0.00124 -0.1170 0.5913 1.0000
1.750 0.7292 0.00548 0.00129 -0.1167 0.5831 1.0000
2.000 0.7553 0.00558 0.00135 -0.1164 0.5750 1.0000
2.250 0.7817 0.00567 0.00141 -0.1161 0.5666 1.0000
2.500 0.8078 0.00578 0.00150 -0.1158 0.5579 1.0000
2.750 0.8330 0.00593 0.00157 -0.1153 0.5385 1.0000
3.000 0.8583 0.00609 0.00166 -0.1148 0.5209 1.0000
3.250 0.8828 0.00629 0.00177 -0.1142 0.4947 1.0000
3.500 0.9068 0.00655 0.00191 -0.1135 0.4636 1.0000
3.750 0.9272 0.00709 0.00214 -0.1122 0.3921 1.0000
4.000 0.9384 0.00849 0.00276 -0.1094 0.2420 1.0000
4.250 0.9529 0.00964 0.00332 -0.1073 0.1331 1.0000
4.500 0.9663 0.01094 0.00414 -0.1048 0.0177 1.0000
4.750 0.9899 0.01128 0.00451 -0.1040 0.0144 1.0000
5.000 1.0113 0.01184 0.00523 -0.1027 0.0113 1.0000
5.250 1.0348 0.01216 0.00557 -0.1020 0.0107 1.0000
5.500 1.0571 0.01261 0.00606 -0.1010 0.0099 1.0000
5.750 1.0786 0.01311 0.00663 -0.0998 0.0090 1.0000
6.000 1.0989 0.01371 0.00729 -0.0984 0.0082 1.0000
6.250 1.1175 0.01444 0.00808 -0.0968 0.0076 1.0000
6.500 1.1330 0.01540 0.00913 -0.0946 0.0072 1.0000
6.750 1.1408 0.01699 0.01081 -0.0912 0.0066 1.0000
7.000 1.1480 0.01911 0.01300 -0.0877 0.0064 1.0000
7.250 1.1701 0.01925 0.01320 -0.0867 0.0061 1.0000
7.500 1.1879 0.02019 0.01420 -0.0850 0.0059 1.0000
7.750 1.2063 0.02114 0.01521 -0.0835 0.0055 1.0000
8.000 1.2253 0.02239 0.01653 -0.0820 0.0051 1.0000
8.250 1.2485 0.02453 0.01877 -0.0812 0.0049 1.0000
8.500 1.2915 0.03510 0.02962 -0.0839 0.0063 1.0000
8.750 1.3066 0.03781 0.03254 -0.0820 0.0063 1.0000
9.000 1.3185 0.04054 0.03550 -0.0797 0.0063 1.0000
9.250 1.3278 0.04323 0.03842 -0.0772 0.0063 1.0000
9.500 1.3337 0.04595 0.04137 -0.0743 0.0063 1.0000
9.750 1.3365 0.04855 0.04421 -0.0711 0.0063 1.0000
10.000 1.3363 0.05103 0.04691 -0.0677 0.0063 1.0000
10.250 1.3329 0.05318 0.04928 -0.0640 0.0062 1.0000
10.500 1.3256 0.05514 0.05143 -0.0598 0.0062 1.0000
10.750 1.3296 0.05349 0.04986 -0.0557 0.0057 1.0000
11.000 1.3239 0.05482 0.05134 -0.0518 0.0054 1.0000
11.250 1.3121 0.05721 0.05390 -0.0483 0.0053 1.0000
11.500 1.2994 0.06005 0.05691 -0.0455 0.0051 1.0000
11.750 1.2848 0.06336 0.06038 -0.0433 0.0050 1.0000
12.000 1.2699 0.06691 0.06408 -0.0419 0.0049 1.0000
12.250 1.2532 0.07097 0.06829 -0.0412 0.0049 1.0000
12.500 1.2346 0.07567 0.07314 -0.0413 0.0048 1.0000
12.750 1.2157 0.08083 0.07845 -0.0423 0.0048 1.0000
13.000 1.1952 0.08674 0.08450 -0.0442 0.0049 1.0000
13.250 1.1753 0.09308 0.09097 -0.0470 0.0049 1.0000
13.500 1.1550 0.10016 0.09818 -0.0507 0.0050 1.0000
13.750 1.1343 0.10805 0.10619 -0.0553 0.0050 1.0000
14.000 1.1136 0.11684 0.11510 -0.0609 0.0052 1.0000
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Polar data table (+)
Polar graphs
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