GOE 409 AIRFOIL (goe409-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 409 AIRFOIL (goe409-il) Reynolds number: 50,000 Max Cl/Cd: 26.56 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe409-il-50000-n5.txt Download as CSV file: xf-goe409-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 409 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7618 0.08653 0.07849 -0.0439 1.0000 0.0842
-12.500 -0.7951 0.07932 0.07118 -0.0473 1.0000 0.0839
-12.250 -0.8259 0.07359 0.06530 -0.0489 1.0000 0.0838
-12.000 -0.8552 0.06895 0.06047 -0.0486 1.0000 0.0838
-11.750 -0.8820 0.06518 0.05647 -0.0467 1.0000 0.0840
-11.500 -0.8928 0.06216 0.05336 -0.0445 1.0000 0.0851
-11.250 -0.8924 0.05987 0.05101 -0.0427 1.0000 0.0867
-11.000 -0.8996 0.05741 0.04840 -0.0399 1.0000 0.0877
-10.750 -0.9038 0.05485 0.04563 -0.0373 1.0000 0.0888
-10.500 -0.9059 0.05232 0.04286 -0.0346 1.0000 0.0898
-10.250 -0.9049 0.05006 0.04034 -0.0320 1.0000 0.0915
-10.000 -0.9027 0.04781 0.03780 -0.0294 1.0000 0.0933
-9.750 -0.8980 0.04562 0.03526 -0.0268 1.0000 0.0950
-9.500 -0.8889 0.04350 0.03279 -0.0246 1.0000 0.0961
-9.250 -0.8748 0.04154 0.03051 -0.0228 1.0000 0.0972
-9.000 -0.8549 0.03984 0.02875 -0.0219 1.0000 0.0986
-8.750 -0.8366 0.03843 0.02727 -0.0207 1.0000 0.1006
-8.500 -0.8195 0.03718 0.02592 -0.0192 1.0000 0.1032
-8.250 -0.8009 0.03593 0.02448 -0.0179 1.0000 0.1060
-8.000 -0.7798 0.03470 0.02305 -0.0167 1.0000 0.1085
-7.750 -0.7580 0.03356 0.02183 -0.0157 1.0000 0.1106
-7.500 -0.7391 0.03256 0.02083 -0.0143 1.0000 0.1129
-7.250 -0.7213 0.03165 0.01987 -0.0127 1.0000 0.1156
-7.000 -0.7044 0.03079 0.01891 -0.0109 1.0000 0.1190
-6.750 -0.6887 0.02999 0.01803 -0.0089 1.0000 0.1236
-6.500 -0.6758 0.02919 0.01727 -0.0066 1.0000 0.1290
-6.250 -0.6619 0.02845 0.01645 -0.0043 1.0000 0.1367
-6.000 -0.6503 0.02762 0.01569 -0.0018 1.0000 0.1449
-5.750 -0.6387 0.02678 0.01488 0.0008 1.0000 0.1571
-5.500 -0.6277 0.02590 0.01409 0.0034 1.0000 0.1750
-5.250 -0.6173 0.02498 0.01333 0.0060 1.0000 0.2033
-5.000 -0.6075 0.02405 0.01265 0.0087 1.0000 0.2447
-4.750 -0.5986 0.02313 0.01212 0.0116 1.0000 0.3012
-4.500 -0.5905 0.02234 0.01184 0.0149 1.0000 0.3779
-4.250 -0.5804 0.02185 0.01168 0.0181 1.0000 0.4582
-4.000 -0.5670 0.02153 0.01148 0.0209 1.0000 0.5099
-3.750 -0.5521 0.02129 0.01139 0.0235 1.0000 0.5550
-3.500 -0.5360 0.02114 0.01134 0.0260 1.0000 0.5940
-3.250 -0.5183 0.02106 0.01131 0.0282 1.0000 0.6271
-3.000 -0.4999 0.02108 0.01144 0.0304 1.0000 0.6654
-2.750 -0.4808 0.02122 0.01167 0.0327 1.0000 0.7065
-2.500 -0.4583 0.02154 0.01208 0.0347 1.0000 0.7467
-2.250 -0.4345 0.02201 0.01260 0.0365 1.0000 0.7869
-2.000 -0.4053 0.02269 0.01327 0.0374 1.0000 0.8237
-1.750 -0.3724 0.02339 0.01392 0.0374 1.0000 0.8546
-1.500 -0.3171 0.02411 0.01451 0.0327 0.9945 0.8755
-1.250 -0.2650 0.02447 0.01475 0.0276 0.9872 0.8902
-1.000 -0.2123 0.02474 0.01490 0.0223 0.9798 0.9032
-0.750 -0.1597 0.02497 0.01504 0.0168 0.9722 0.9158
-0.500 -0.1054 0.02508 0.01509 0.0111 0.9638 0.9256
-0.250 -0.0522 0.02516 0.01513 0.0054 0.9552 0.9357
0.000 0.0000 0.02522 0.01517 0.0000 0.9463 0.9463
0.250 0.0521 0.02516 0.01513 -0.0054 0.9358 0.9552
0.500 0.1056 0.02508 0.01509 -0.0111 0.9256 0.9638
0.750 0.1599 0.02497 0.01504 -0.0169 0.9158 0.9722
1.000 0.2124 0.02474 0.01490 -0.0223 0.9032 0.9799
1.250 0.2650 0.02447 0.01475 -0.0276 0.8902 0.9873
1.500 0.3171 0.02411 0.01451 -0.0327 0.8756 0.9945
1.750 0.3723 0.02338 0.01392 -0.0374 0.8546 1.0000
2.000 0.4050 0.02270 0.01328 -0.0374 0.8240 1.0000
2.250 0.4344 0.02200 0.01259 -0.0365 0.7869 1.0000
2.500 0.4582 0.02154 0.01209 -0.0347 0.7471 1.0000
2.750 0.4805 0.02121 0.01166 -0.0327 0.7052 1.0000
3.000 0.4998 0.02107 0.01143 -0.0304 0.6650 1.0000
3.250 0.5181 0.02105 0.01131 -0.0281 0.6264 1.0000
3.500 0.5358 0.02114 0.01133 -0.0260 0.5937 1.0000
3.750 0.5519 0.02129 0.01138 -0.0235 0.5543 1.0000
4.000 0.5669 0.02153 0.01148 -0.0209 0.5101 1.0000
4.250 0.5803 0.02185 0.01168 -0.0181 0.4584 1.0000
4.500 0.5905 0.02234 0.01183 -0.0149 0.3783 1.0000
4.750 0.5984 0.02313 0.01211 -0.0116 0.3008 1.0000
5.000 0.6074 0.02404 0.01265 -0.0087 0.2452 1.0000
5.250 0.6173 0.02497 0.01333 -0.0060 0.2036 1.0000
5.500 0.6277 0.02589 0.01409 -0.0034 0.1751 1.0000
5.750 0.6386 0.02678 0.01488 -0.0008 0.1571 1.0000
6.000 0.6503 0.02761 0.01569 0.0018 0.1451 1.0000
6.250 0.6619 0.02844 0.01644 0.0043 0.1368 1.0000
6.500 0.6758 0.02919 0.01726 0.0066 0.1290 1.0000
6.750 0.6886 0.02998 0.01802 0.0089 0.1236 1.0000
7.000 0.7044 0.03079 0.01891 0.0109 0.1190 1.0000
7.250 0.7214 0.03165 0.01987 0.0127 0.1156 1.0000
7.500 0.7391 0.03256 0.02083 0.0143 0.1128 1.0000
7.750 0.7580 0.03356 0.02182 0.0157 0.1105 1.0000
8.000 0.7799 0.03469 0.02305 0.0167 0.1085 1.0000
8.250 0.8009 0.03592 0.02449 0.0179 0.1060 1.0000
8.500 0.8195 0.03717 0.02591 0.0192 0.1032 1.0000
8.750 0.8368 0.03844 0.02728 0.0206 0.1007 1.0000
9.000 0.8549 0.03984 0.02875 0.0219 0.0986 1.0000
9.250 0.8749 0.04153 0.03050 0.0228 0.0972 1.0000
9.500 0.8889 0.04350 0.03279 0.0245 0.0961 1.0000
9.750 0.8982 0.04562 0.03526 0.0268 0.0950 1.0000
10.000 0.9030 0.04783 0.03782 0.0293 0.0934 1.0000
10.250 0.9052 0.05004 0.04032 0.0320 0.0914 1.0000
10.500 0.9062 0.05232 0.04285 0.0346 0.0898 1.0000
10.750 0.9043 0.05485 0.04563 0.0372 0.0887 1.0000
11.000 0.9000 0.05743 0.04842 0.0398 0.0877 1.0000
11.250 0.8931 0.05987 0.05101 0.0426 0.0866 1.0000
11.500 0.8952 0.06215 0.05333 0.0443 0.0849 1.0000
11.750 0.8823 0.06522 0.05651 0.0466 0.0840 1.0000
12.000 0.8554 0.06900 0.06052 0.0485 0.0838 1.0000
12.250 0.8260 0.07365 0.06536 0.0488 0.0837 1.0000
12.500 0.7933 0.07955 0.07141 0.0471 0.0838 1.0000
12.750 0.7609 0.08678 0.07875 0.0436 0.0841 1.0000
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