GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 546 AIRFOIL (goe546-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.65 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe546-il-1000000.txt Download as CSV file: xf-goe546-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 546 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7443 0.06960 0.06777 -0.0585 1.0000 0.0130
-13.000 -0.9214 0.03592 0.03357 -0.0837 1.0000 0.0121
-12.750 -0.9340 0.03314 0.03063 -0.0820 1.0000 0.0122
-12.500 -0.9424 0.03058 0.02788 -0.0798 1.0000 0.0123
-12.250 -0.9441 0.02873 0.02587 -0.0773 1.0000 0.0124
-12.000 -0.9175 0.02674 0.02364 -0.0798 0.9982 0.0126
-11.750 -0.8958 0.02337 0.01993 -0.0829 0.9955 0.0132
-11.500 -0.8646 0.02250 0.01900 -0.0847 0.9941 0.0136
-11.250 -0.8349 0.02195 0.01841 -0.0859 0.9917 0.0139
-11.000 -0.8034 0.02143 0.01784 -0.0873 0.9893 0.0144
-10.750 -0.7716 0.02070 0.01701 -0.0889 0.9871 0.0149
-10.500 -0.7394 0.01988 0.01604 -0.0906 0.9854 0.0155
-10.250 -0.7063 0.01923 0.01527 -0.0923 0.9841 0.0158
-10.000 -0.6844 0.01745 0.01330 -0.0926 0.9783 0.0165
-9.750 -0.6522 0.01715 0.01299 -0.0938 0.9757 0.0171
-9.500 -0.6191 0.01688 0.01269 -0.0952 0.9737 0.0177
-9.250 -0.5861 0.01634 0.01207 -0.0967 0.9721 0.0183
-9.000 -0.5601 0.01580 0.01143 -0.0966 0.9651 0.0189
-8.750 -0.5267 0.01551 0.01105 -0.0979 0.9619 0.0194
-8.500 -0.4940 0.01429 0.00971 -0.0998 0.9592 0.0205
-8.250 -0.4628 0.01410 0.00952 -0.1006 0.9528 0.0212
-8.000 -0.4288 0.01379 0.00916 -0.1021 0.9482 0.0220
-7.750 -0.3950 0.01338 0.00866 -0.1036 0.9436 0.0229
-7.500 -0.3638 0.01308 0.00828 -0.1044 0.9369 0.0236
-7.250 -0.3336 0.01226 0.00732 -0.1053 0.9307 0.0245
-7.000 -0.3065 0.01179 0.00682 -0.1053 0.9232 0.0255
-6.750 -0.2774 0.01154 0.00652 -0.1057 0.9167 0.0263
-6.500 -0.2508 0.01125 0.00618 -0.1055 0.9102 0.0272
-6.250 -0.2237 0.01099 0.00585 -0.1053 0.9043 0.0281
-6.000 -0.1959 0.01084 0.00563 -0.1053 0.8990 0.0289
-5.750 -0.1697 0.01066 0.00540 -0.1049 0.8933 0.0294
-5.500 -0.1463 0.00977 0.00443 -0.1042 0.8874 0.0307
-5.250 -0.1199 0.00950 0.00414 -0.1040 0.8823 0.0317
-5.000 -0.0937 0.00930 0.00392 -0.1036 0.8769 0.0328
-4.750 -0.0671 0.00907 0.00364 -0.1033 0.8716 0.0338
-4.500 -0.0406 0.00887 0.00339 -0.1029 0.8657 0.0347
-4.250 -0.0145 0.00868 0.00316 -0.1025 0.8586 0.0354
-4.000 0.0117 0.00843 0.00285 -0.1021 0.8518 0.0364
-3.750 0.0372 0.00808 0.00247 -0.1015 0.8453 0.0383
-3.500 0.0640 0.00792 0.00226 -0.1012 0.8394 0.0398
-3.250 0.0909 0.00777 0.00210 -0.1009 0.8335 0.0414
-3.000 0.1178 0.00764 0.00194 -0.1006 0.8270 0.0431
-2.750 0.1447 0.00749 0.00175 -0.1003 0.8208 0.0460
-2.500 0.1714 0.00732 0.00160 -0.0999 0.8136 0.0508
-2.250 0.1982 0.00720 0.00146 -0.0996 0.8065 0.0587
-2.000 0.2248 0.00701 0.00134 -0.0993 0.7985 0.0785
-1.750 0.2500 0.00666 0.00121 -0.0988 0.7906 0.1546
-1.500 0.2745 0.00620 0.00114 -0.0983 0.7811 0.2785
-1.250 0.3001 0.00599 0.00109 -0.0978 0.7704 0.3453
-1.000 0.3256 0.00585 0.00106 -0.0973 0.7581 0.4018
-0.750 0.3513 0.00577 0.00105 -0.0968 0.7437 0.4467
-0.500 0.3770 0.00573 0.00104 -0.0962 0.7277 0.4815
-0.250 0.4024 0.00569 0.00104 -0.0956 0.7100 0.5173
0.000 0.4272 0.00563 0.00107 -0.0949 0.6933 0.5688
0.250 0.4512 0.00551 0.00111 -0.0941 0.6780 0.6409
0.500 0.4735 0.00532 0.00116 -0.0928 0.6642 0.7382
0.750 0.4925 0.00504 0.00126 -0.0905 0.6516 0.8826
1.000 0.5382 0.00504 0.00132 -0.0943 0.6371 0.9618
1.250 0.5870 0.00518 0.00136 -0.0990 0.6161 0.9900
1.500 0.6193 0.00533 0.00142 -0.1000 0.5979 1.0000
1.750 0.6434 0.00543 0.00146 -0.0992 0.5862 1.0000
2.000 0.6675 0.00554 0.00152 -0.0983 0.5740 1.0000
2.250 0.6915 0.00566 0.00157 -0.0974 0.5592 1.0000
2.500 0.7155 0.00578 0.00164 -0.0965 0.5423 1.0000
2.750 0.7392 0.00593 0.00171 -0.0956 0.5218 1.0000
3.000 0.7621 0.00613 0.00180 -0.0945 0.4966 1.0000
3.250 0.7841 0.00639 0.00192 -0.0933 0.4642 1.0000
3.500 0.8057 0.00669 0.00207 -0.0920 0.4297 1.0000
3.750 0.8280 0.00698 0.00222 -0.0909 0.3995 1.0000
4.000 0.8498 0.00732 0.00240 -0.0897 0.3647 1.0000
4.250 0.8694 0.00781 0.00264 -0.0882 0.3104 1.0000
4.500 0.8872 0.00845 0.00296 -0.0864 0.2480 1.0000
4.750 0.9068 0.00898 0.00327 -0.0849 0.2050 1.0000
5.000 0.9227 0.00978 0.00369 -0.0828 0.1320 1.0000
5.250 0.9384 0.01061 0.00420 -0.0807 0.0731 1.0000
5.500 0.9575 0.01119 0.00459 -0.0791 0.0422 1.0000
5.750 0.9802 0.01151 0.00489 -0.0781 0.0389 1.0000
6.000 1.0026 0.01183 0.00522 -0.0771 0.0363 1.0000
6.250 1.0248 0.01217 0.00558 -0.0761 0.0347 1.0000
6.500 1.0476 0.01246 0.00588 -0.0751 0.0339 1.0000
6.750 1.0697 0.01278 0.00623 -0.0741 0.0332 1.0000
7.000 1.0913 0.01312 0.00660 -0.0730 0.0323 1.0000
7.250 1.1123 0.01349 0.00700 -0.0718 0.0314 1.0000
7.500 1.1323 0.01391 0.00744 -0.0705 0.0304 1.0000
7.750 1.1508 0.01442 0.00797 -0.0688 0.0293 1.0000
8.000 1.1645 0.01518 0.00882 -0.0664 0.0281 1.0000
8.250 1.1833 0.01556 0.00923 -0.0648 0.0276 1.0000
8.500 1.2010 0.01592 0.00962 -0.0631 0.0272 1.0000
8.750 1.2173 0.01634 0.01008 -0.0611 0.0266 1.0000
9.000 1.2333 0.01677 0.01056 -0.0591 0.0260 1.0000
9.250 1.2493 0.01722 0.01103 -0.0571 0.0252 1.0000
9.500 1.2650 0.01769 0.01152 -0.0552 0.0244 1.0000
9.750 1.2786 0.01828 0.01214 -0.0530 0.0238 1.0000
10.000 1.2882 0.01911 0.01301 -0.0503 0.0230 1.0000
10.250 1.2897 0.02046 0.01445 -0.0466 0.0222 1.0000
10.500 1.3095 0.02072 0.01474 -0.0455 0.0218 1.0000
10.750 1.3255 0.02122 0.01529 -0.0440 0.0213 1.0000
11.000 1.3412 0.02176 0.01587 -0.0425 0.0206 1.0000
11.250 1.3561 0.02235 0.01651 -0.0410 0.0200 1.0000
11.500 1.3699 0.02303 0.01722 -0.0394 0.0194 1.0000
11.750 1.3833 0.02375 0.01797 -0.0379 0.0189 1.0000
12.000 1.3927 0.02476 0.01901 -0.0360 0.0184 1.0000
12.250 1.3948 0.02636 0.02068 -0.0335 0.0176 1.0000
12.500 1.4099 0.02703 0.02141 -0.0324 0.0173 1.0000
12.750 1.4231 0.02787 0.02232 -0.0312 0.0168 1.0000
13.000 1.4361 0.02875 0.02326 -0.0300 0.0163 1.0000
13.250 1.4492 0.02963 0.02418 -0.0289 0.0158 1.0000
13.500 1.4601 0.03072 0.02531 -0.0277 0.0154 1.0000
13.750 1.4718 0.03176 0.02638 -0.0267 0.0149 1.0000
14.000 1.4769 0.03340 0.02807 -0.0254 0.0145 1.0000
14.250 1.4717 0.03602 0.03079 -0.0236 0.0140 1.0000
14.500 1.4819 0.03734 0.03219 -0.0228 0.0138 1.0000
14.750 1.4889 0.03900 0.03394 -0.0220 0.0135 1.0000
15.000 1.4974 0.04054 0.03555 -0.0214 0.0130 1.0000
15.250 1.5028 0.04247 0.03756 -0.0208 0.0127 1.0000
15.500 1.5101 0.04426 0.03941 -0.0204 0.0124 1.0000
15.750 1.5168 0.04616 0.04136 -0.0202 0.0120 1.0000
16.000 1.5188 0.04864 0.04391 -0.0199 0.0117 1.0000
16.250 1.5184 0.05150 0.04684 -0.0199 0.0115 1.0000
16.500 1.5103 0.05540 0.05085 -0.0201 0.0112 1.0000
16.750 1.5006 0.05964 0.05521 -0.0205 0.0109 1.0000
17.000 1.5004 0.06282 0.05849 -0.0210 0.0108 1.0000
17.250 1.4993 0.06619 0.06197 -0.0217 0.0107 1.0000
17.500 1.4950 0.07010 0.06600 -0.0227 0.0105 1.0000
17.750 1.4904 0.07416 0.07017 -0.0238 0.0104 1.0000
18.000 1.4845 0.07853 0.07466 -0.0252 0.0102 1.0000
18.250 1.4774 0.08323 0.07946 -0.0269 0.0101 1.0000
18.500 1.4717 0.08785 0.08419 -0.0287 0.0098 1.0000
18.750 1.4611 0.09332 0.08978 -0.0309 0.0098 1.0000
19.000 1.4512 0.09887 0.09544 -0.0334 0.0097 1.0000
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Polar data table (+)
Polar graphs
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