GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 478 AIRFOIL (goe478-il) Reynolds number: 100,000 Max Cl/Cd: 51.65 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe478-il-100000.txt Download as CSV file: xf-goe478-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 478 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3649 0.11425 0.10956 -0.0242 1.0000 0.1213
-8.250 -0.4098 0.11480 0.11022 -0.0243 1.0000 0.1224
-8.000 -0.4521 0.11445 0.10996 -0.0257 0.9982 0.1227
-7.750 -0.3896 0.10744 0.10290 -0.0222 0.9982 0.1248
-7.500 -0.3595 0.10389 0.09933 -0.0242 0.9942 0.1284
-7.250 -0.3502 0.10078 0.09622 -0.0283 0.9883 0.1333
-7.000 -0.3989 0.09741 0.09281 -0.0446 0.9735 0.1374
-6.750 -0.3539 0.09334 0.08881 -0.0391 0.9723 0.1393
-6.500 -0.3250 0.09022 0.08568 -0.0398 0.9676 0.1428
-6.250 -0.3177 0.08716 0.08261 -0.0428 0.9600 0.1471
-6.000 -0.3374 0.08219 0.07753 -0.0529 0.9493 0.1535
-5.750 -0.3118 0.07932 0.07472 -0.0512 0.9454 0.1556
-5.500 -0.2832 0.07626 0.07163 -0.0538 0.9414 0.1604
-5.250 -0.2968 0.07249 0.06762 -0.0594 0.9303 0.1697
-5.000 -0.2664 0.06933 0.06456 -0.0596 0.9267 0.1724
-4.750 -0.2570 0.06740 0.06264 -0.0582 0.9189 0.1769
-4.500 -0.2386 0.06360 0.05865 -0.0629 0.9118 0.1886
-4.250 -0.2139 0.06138 0.05644 -0.0635 0.9062 0.1956
-4.000 -0.2075 0.04448 0.03745 -0.0714 0.8976 0.1099
-3.750 -0.1703 0.04152 0.03435 -0.0738 0.8929 0.1070
-3.500 -0.1521 0.03920 0.03173 -0.0727 0.8846 0.1051
-3.250 -0.1208 0.03683 0.02892 -0.0736 0.8778 0.1052
-3.000 -0.0768 0.03464 0.02621 -0.0762 0.8737 0.1073
-2.750 -0.0615 0.03358 0.02484 -0.0739 0.8626 0.1082
-2.500 -0.0187 0.03179 0.02274 -0.0761 0.8575 0.1106
-2.250 0.0061 0.03103 0.02196 -0.0755 0.8480 0.1139
-2.000 0.0446 0.03011 0.02088 -0.0769 0.8410 0.1211
-1.750 0.0953 0.02870 0.01948 -0.0803 0.8374 0.1300
-1.500 0.1129 0.02830 0.01899 -0.0781 0.8246 0.1382
-1.250 0.1616 0.02720 0.01807 -0.0811 0.8206 0.1580
-1.000 0.1829 0.02692 0.01787 -0.0796 0.8087 0.1795
-0.750 0.2291 0.02579 0.01691 -0.0821 0.8039 0.2268
-0.500 0.2810 0.02447 0.01586 -0.0856 0.8010 0.2809
-0.250 0.2974 0.02414 0.01579 -0.0833 0.7875 0.3231
0.000 0.3380 0.02196 0.01519 -0.0845 0.7840 0.6467
0.500 0.5153 0.02072 0.01398 -0.1056 0.7719 1.0000
0.750 0.5579 0.02026 0.01333 -0.1074 0.7653 1.0000
1.000 0.5736 0.02052 0.01349 -0.1049 0.7521 1.0000
1.250 0.6160 0.02010 0.01290 -0.1066 0.7459 1.0000
1.500 0.6291 0.02045 0.01318 -0.1037 0.7322 1.0000
1.750 0.6715 0.02006 0.01263 -0.1055 0.7264 1.0000
2.000 0.6807 0.02058 0.01311 -0.1021 0.7127 1.0000
2.250 0.7122 0.02052 0.01294 -0.1021 0.7048 1.0000
2.500 0.7297 0.02081 0.01319 -0.1000 0.6936 1.0000
2.750 0.7561 0.02092 0.01322 -0.0994 0.6852 1.0000
3.000 0.7761 0.02117 0.01342 -0.0977 0.6752 1.0000
3.250 0.8018 0.02128 0.01348 -0.0969 0.6669 1.0000
3.500 0.8221 0.02152 0.01368 -0.0953 0.6573 1.0000
3.750 0.8477 0.02160 0.01371 -0.0945 0.6490 1.0000
4.000 0.8709 0.02164 0.01372 -0.0933 0.6393 1.0000
4.250 0.8926 0.02175 0.01380 -0.0917 0.6295 1.0000
4.500 0.9237 0.02149 0.01348 -0.0916 0.6206 1.0000
4.750 0.9410 0.02176 0.01375 -0.0895 0.6101 1.0000
5.000 0.9776 0.02138 0.01326 -0.0903 0.6021 1.0000
5.250 0.9920 0.02177 0.01369 -0.0877 0.5911 1.0000
5.500 1.0228 0.02164 0.01348 -0.0877 0.5820 1.0000
5.750 1.0457 0.02176 0.01359 -0.0865 0.5714 1.0000
6.000 1.0682 0.02198 0.01381 -0.0852 0.5608 1.0000
6.250 1.1046 0.02185 0.01352 -0.0861 0.5506 1.0000
6.500 1.1182 0.02233 0.01407 -0.0835 0.5386 1.0000
6.750 1.1423 0.02262 0.01434 -0.0825 0.5272 1.0000
7.000 1.1752 0.02277 0.01435 -0.0830 0.5155 1.0000
7.250 1.1872 0.02330 0.01497 -0.0801 0.5026 1.0000
7.500 1.2073 0.02372 0.01540 -0.0785 0.4899 1.0000
7.750 1.2322 0.02401 0.01560 -0.0777 0.4764 1.0000
8.000 1.2525 0.02425 0.01579 -0.0761 0.4614 1.0000
8.250 1.2627 0.02457 0.01615 -0.0728 0.4457 1.0000
8.500 1.2735 0.02484 0.01646 -0.0696 0.4297 1.0000
8.750 1.2834 0.02509 0.01671 -0.0662 0.4135 1.0000
9.000 1.2919 0.02537 0.01700 -0.0627 0.3973 1.0000
9.250 1.2985 0.02571 0.01733 -0.0590 0.3809 1.0000
9.500 1.3016 0.02609 0.01770 -0.0547 0.3646 1.0000
9.750 1.3029 0.02657 0.01815 -0.0503 0.3480 1.0000
10.000 1.3039 0.02719 0.01872 -0.0461 0.3309 1.0000
10.250 1.3055 0.02794 0.01942 -0.0423 0.3139 1.0000
10.500 1.3070 0.02885 0.02025 -0.0387 0.2969 1.0000
10.750 1.3094 0.02989 0.02120 -0.0355 0.2807 1.0000
11.000 1.3125 0.03107 0.02229 -0.0326 0.2651 1.0000
11.250 1.3165 0.03235 0.02347 -0.0300 0.2503 1.0000
11.500 1.3221 0.03370 0.02471 -0.0277 0.2364 1.0000
11.750 1.3294 0.03508 0.02596 -0.0257 0.2233 1.0000
12.000 1.3398 0.03645 0.02715 -0.0240 0.2104 1.0000
12.250 1.3413 0.03809 0.02891 -0.0217 0.1995 1.0000
12.500 1.3497 0.03968 0.03046 -0.0201 0.1891 1.0000
12.750 1.3678 0.04099 0.03158 -0.0193 0.1791 1.0000
13.000 1.3696 0.04280 0.03357 -0.0173 0.1716 1.0000
13.250 1.3896 0.04414 0.03476 -0.0167 0.1637 1.0000
13.500 1.3916 0.04604 0.03686 -0.0149 0.1578 1.0000
13.750 1.4252 0.04709 0.03763 -0.0154 0.1507 1.0000
14.000 1.4211 0.04929 0.04014 -0.0132 0.1472 1.0000
14.250 1.4260 0.05123 0.04224 -0.0119 0.1430 1.0000
14.500 1.4560 0.05231 0.04314 -0.0121 0.1379 1.0000
14.750 1.4577 0.05472 0.04576 -0.0106 0.1351 1.0000
15.000 1.4528 0.05733 0.04865 -0.0090 0.1326 1.0000
15.250 1.4512 0.05988 0.05139 -0.0077 0.1301 1.0000
15.500 1.4581 0.06195 0.05354 -0.0069 0.1273 1.0000
15.750 1.4873 0.06354 0.05503 -0.0071 0.1236 1.0000
16.000 1.4663 0.06723 0.05905 -0.0054 0.1226 1.0000
16.250 1.4445 0.07143 0.06356 -0.0044 0.1215 1.0000
16.500 1.4200 0.07620 0.06863 -0.0039 0.1205 1.0000
16.750 1.3914 0.08175 0.07447 -0.0041 0.1198 1.0000
17.000 1.3529 0.08889 0.08192 -0.0054 0.1195 1.0000
17.250 1.2897 0.10023 0.09362 -0.0094 0.1202 1.0000
17.500 1.1301 0.13193 0.12574 -0.0261 0.1238 1.0000
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