GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 547 AIRFOIL (goe547-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.69 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe547-il-1000000-n5.txt Download as CSV file: xf-goe547-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 547 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -1.0109 0.03538 0.03284 -0.1011 0.9979 0.0072
-14.250 -1.0061 0.03089 0.02809 -0.1065 0.9939 0.0073
-14.000 -0.9941 0.02827 0.02528 -0.1084 0.9905 0.0076
-13.750 -0.9760 0.02621 0.02303 -0.1100 0.9879 0.0078
-13.500 -0.9537 0.02451 0.02115 -0.1117 0.9862 0.0081
-13.250 -0.9357 0.02289 0.01940 -0.1121 0.9830 0.0086
-13.000 -0.9150 0.02159 0.01797 -0.1125 0.9796 0.0091
-12.750 -0.8907 0.02043 0.01670 -0.1133 0.9775 0.0098
-12.500 -0.8641 0.01941 0.01556 -0.1143 0.9759 0.0104
-12.250 -0.8435 0.01857 0.01461 -0.1138 0.9716 0.0108
-12.000 -0.8189 0.01785 0.01383 -0.1140 0.9680 0.0117
-11.750 -0.7911 0.01726 0.01320 -0.1147 0.9657 0.0128
-11.500 -0.7618 0.01667 0.01254 -0.1156 0.9641 0.0137
-11.250 -0.7402 0.01612 0.01191 -0.1149 0.9576 0.0143
-11.000 -0.7089 0.01592 0.01173 -0.1159 0.9545 0.0154
-10.500 -0.6414 0.01548 0.01124 -0.1190 0.9471 0.0172
-10.250 -0.6062 0.01509 0.01078 -0.1210 0.9416 0.0179
-10.000 -0.5692 0.01467 0.01027 -0.1233 0.9363 0.0185
-9.750 -0.5355 0.01443 0.00995 -0.1248 0.9286 0.0188
-9.500 -0.5041 0.01385 0.00928 -0.1262 0.9215 0.0196
-9.250 -0.4751 0.01358 0.00895 -0.1267 0.9137 0.0201
-9.000 -0.4460 0.01333 0.00864 -0.1273 0.9066 0.0206
-8.750 -0.4190 0.01315 0.00840 -0.1273 0.8990 0.0211
-8.500 -0.3917 0.01295 0.00813 -0.1273 0.8922 0.0217
-8.250 -0.3660 0.01274 0.00787 -0.1271 0.8856 0.0223
-8.000 -0.3400 0.01251 0.00756 -0.1269 0.8793 0.0229
-7.750 -0.3149 0.01220 0.00716 -0.1265 0.8732 0.0233
-7.500 -0.2892 0.01198 0.00687 -0.1262 0.8668 0.0238
-7.250 -0.2639 0.01168 0.00649 -0.1258 0.8612 0.0241
-7.000 -0.2385 0.01142 0.00617 -0.1254 0.8556 0.0244
-6.750 -0.2129 0.01118 0.00586 -0.1250 0.8500 0.0246
-6.500 -0.1875 0.01090 0.00551 -0.1246 0.8448 0.0248
-6.250 -0.1621 0.01063 0.00518 -0.1242 0.8388 0.0249
-5.750 -0.1124 0.00991 0.00431 -0.1232 0.8280 0.0253
-5.500 -0.0881 0.00948 0.00378 -0.1225 0.8225 0.0258
-5.250 -0.0630 0.00916 0.00339 -0.1220 0.8173 0.0266
-5.000 -0.0373 0.00890 0.00310 -0.1216 0.8117 0.0274
-4.750 -0.0115 0.00871 0.00286 -0.1212 0.8057 0.0279
-4.500 0.0147 0.00854 0.00264 -0.1209 0.8001 0.0284
-4.250 0.0410 0.00838 0.00245 -0.1205 0.7943 0.0288
-3.750 0.0936 0.00811 0.00210 -0.1199 0.7825 0.0298
-3.500 0.1198 0.00800 0.00195 -0.1195 0.7757 0.0302
-3.250 0.1463 0.00790 0.00181 -0.1192 0.7694 0.0306
-3.000 0.1727 0.00780 0.00168 -0.1188 0.7626 0.0311
-2.750 0.1991 0.00773 0.00156 -0.1185 0.7558 0.0315
-2.500 0.2255 0.00765 0.00146 -0.1182 0.7481 0.0320
-2.250 0.2518 0.00760 0.00137 -0.1178 0.7408 0.0324
-2.000 0.2783 0.00755 0.00129 -0.1174 0.7327 0.0330
-1.750 0.3045 0.00749 0.00121 -0.1170 0.7248 0.0358
-1.500 0.3296 0.00745 0.00115 -0.1164 0.7121 0.0416
-1.250 0.3542 0.00738 0.00112 -0.1157 0.6978 0.0665
-1.000 0.3793 0.00737 0.00109 -0.1151 0.6841 0.0746
-0.750 0.4048 0.00739 0.00106 -0.1146 0.6712 0.0787
-0.500 0.4302 0.00739 0.00104 -0.1140 0.6590 0.0857
-0.250 0.4551 0.00741 0.00103 -0.1134 0.6451 0.0954
0.000 0.4784 0.00720 0.00104 -0.1126 0.6314 0.1882
0.250 0.5031 0.00721 0.00106 -0.1119 0.6178 0.2120
0.500 0.5281 0.00722 0.00108 -0.1113 0.6062 0.2319
0.750 0.5526 0.00720 0.00112 -0.1106 0.5937 0.2690
1.000 0.5777 0.00716 0.00116 -0.1101 0.5824 0.3076
1.250 0.6026 0.00709 0.00121 -0.1096 0.5737 0.3615
1.500 0.6263 0.00697 0.00129 -0.1088 0.5642 0.4497
1.750 0.6513 0.00692 0.00136 -0.1082 0.5544 0.4986
2.000 0.6759 0.00695 0.00143 -0.1076 0.5427 0.5309
2.250 0.7001 0.00699 0.00151 -0.1068 0.5282 0.5598
2.500 0.7213 0.00716 0.00163 -0.1055 0.4950 0.5916
2.750 0.7415 0.00733 0.00177 -0.1039 0.4613 0.6376
3.000 0.7602 0.00747 0.00194 -0.1021 0.4260 0.7010
3.500 0.8386 0.00801 0.00263 -0.1080 0.3183 1.0000
3.750 0.8580 0.00832 0.00282 -0.1063 0.2916 1.0000
4.000 0.8770 0.00866 0.00302 -0.1046 0.2637 1.0000
4.250 0.8962 0.00900 0.00323 -0.1029 0.2369 1.0000
4.500 0.9159 0.00930 0.00343 -0.1013 0.2152 1.0000
4.750 0.9354 0.00962 0.00364 -0.0997 0.1925 1.0000
5.000 0.9473 0.01032 0.00402 -0.0967 0.1313 1.0000
5.250 0.9664 0.01065 0.00429 -0.0950 0.1155 1.0000
5.500 0.9863 0.01094 0.00453 -0.0935 0.1057 1.0000
5.750 1.0074 0.01115 0.00474 -0.0922 0.1002 1.0000
6.000 1.0257 0.01145 0.00499 -0.0904 0.0906 1.0000
6.250 1.0405 0.01188 0.00529 -0.0879 0.0664 1.0000
6.500 1.0566 0.01226 0.00561 -0.0857 0.0531 1.0000
6.750 1.0740 0.01260 0.00592 -0.0838 0.0466 1.0000
7.000 1.0922 0.01292 0.00622 -0.0820 0.0399 1.0000
7.250 1.1050 0.01351 0.00670 -0.0793 0.0211 1.0000
7.500 1.1210 0.01396 0.00711 -0.0773 0.0150 1.0000
7.750 1.1386 0.01434 0.00750 -0.0755 0.0133 1.0000
8.000 1.1554 0.01476 0.00794 -0.0736 0.0115 1.0000
8.250 1.1732 0.01514 0.00835 -0.0719 0.0109 1.0000
8.500 1.1908 0.01553 0.00877 -0.0703 0.0102 1.0000
8.750 1.2080 0.01595 0.00922 -0.0686 0.0097 1.0000
9.000 1.2242 0.01643 0.00972 -0.0668 0.0090 1.0000
9.250 1.2397 0.01696 0.01027 -0.0649 0.0084 1.0000
9.500 1.2546 0.01753 0.01088 -0.0630 0.0079 1.0000
9.750 1.2706 0.01805 0.01143 -0.0613 0.0076 1.0000
10.000 1.2862 0.01860 0.01202 -0.0596 0.0073 1.0000
10.250 1.3013 0.01918 0.01265 -0.0579 0.0069 1.0000
10.500 1.3156 0.01983 0.01335 -0.0561 0.0067 1.0000
10.750 1.3297 0.02050 0.01405 -0.0544 0.0064 1.0000
11.000 1.3428 0.02125 0.01484 -0.0526 0.0061 1.0000
11.250 1.3549 0.02209 0.01572 -0.0507 0.0059 1.0000
11.500 1.3648 0.02310 0.01679 -0.0487 0.0056 1.0000
11.750 1.3772 0.02396 0.01770 -0.0470 0.0055 1.0000
12.000 1.3899 0.02480 0.01861 -0.0455 0.0053 1.0000
12.250 1.4008 0.02580 0.01967 -0.0438 0.0052 1.0000
12.500 1.4116 0.02683 0.02076 -0.0422 0.0051 1.0000
12.750 1.4214 0.02795 0.02195 -0.0406 0.0049 1.0000
13.000 1.4324 0.02901 0.02305 -0.0392 0.0047 1.0000
13.250 1.4419 0.03019 0.02430 -0.0377 0.0046 1.0000
13.500 1.4494 0.03157 0.02575 -0.0361 0.0045 1.0000
13.750 1.4586 0.03283 0.02706 -0.0349 0.0043 1.0000
14.000 1.4643 0.03444 0.02877 -0.0334 0.0043 1.0000
14.250 1.4704 0.03604 0.03043 -0.0320 0.0042 1.0000
14.500 1.4759 0.03774 0.03219 -0.0308 0.0041 1.0000
14.750 1.4790 0.03972 0.03427 -0.0296 0.0041 1.0000
15.000 1.4791 0.04207 0.03670 -0.0284 0.0039 1.0000
15.250 1.4782 0.04459 0.03933 -0.0273 0.0039 1.0000
15.500 1.4775 0.04719 0.04203 -0.0265 0.0038 1.0000
15.750 1.4790 0.04965 0.04458 -0.0258 0.0038 1.0000
16.000 1.4797 0.05227 0.04730 -0.0254 0.0037 1.0000
16.250 1.4798 0.05502 0.05015 -0.0250 0.0037 1.0000
16.500 1.4790 0.05797 0.05320 -0.0248 0.0036 1.0000
16.750 1.4738 0.06155 0.05690 -0.0249 0.0036 1.0000
17.000 1.4723 0.06478 0.06023 -0.0250 0.0036 1.0000
17.250 1.4657 0.06873 0.06430 -0.0254 0.0035 1.0000
17.500 1.4624 0.07236 0.06803 -0.0260 0.0035 1.0000
17.750 1.4519 0.07716 0.07297 -0.0269 0.0035 1.0000
18.000 1.4478 0.08115 0.07705 -0.0279 0.0034 1.0000
18.250 1.4356 0.08647 0.08250 -0.0294 0.0034 1.0000
18.500 1.4228 0.09213 0.08829 -0.0313 0.0034 1.0000
18.750 1.4104 0.09788 0.09417 -0.0335 0.0034 1.0000
19.000 1.3989 0.10368 0.10009 -0.0358 0.0034 1.0000
19.250 1.3836 0.11029 0.10683 -0.0388 0.0033 1.0000
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