GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 492 AIRFOIL (goe492-il) Reynolds number: 500,000 Max Cl/Cd: 99.43 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe492-il-500000-n5.txt Download as CSV file: xf-goe492-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 492 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3245 0.07692 0.07490 -0.0328 1.0000 0.0054
-8.250 -0.3187 0.07227 0.07025 -0.0357 0.9981 0.0053
-8.000 -0.4070 0.08572 0.08358 -0.0305 1.0000 0.0055
-7.500 -0.3977 0.07841 0.07632 -0.0360 0.9945 0.0051
-7.250 -0.3789 0.07274 0.07065 -0.0440 0.9888 0.0049
-7.000 -0.3584 0.06649 0.06439 -0.0533 0.9828 0.0047
-6.750 -0.3313 0.05913 0.05699 -0.0649 0.9781 0.0045
-6.500 -0.3026 0.05002 0.04778 -0.0775 0.9709 0.0042
-6.250 -0.2719 0.02129 0.01765 -0.0985 0.9596 0.0037
-6.000 -0.2434 0.01782 0.01361 -0.1003 0.9559 0.0039
-5.750 -0.2163 0.01583 0.01123 -0.1009 0.9508 0.0042
-5.500 -0.1883 0.01426 0.00932 -0.1013 0.9455 0.0046
-5.250 -0.1586 0.01294 0.00770 -0.1020 0.9417 0.0051
-5.000 -0.1310 0.01233 0.00692 -0.1020 0.9371 0.0058
-4.750 -0.1041 0.01107 0.00541 -0.1021 0.9322 0.0067
-4.500 -0.0753 0.01037 0.00454 -0.1024 0.9282 0.0077
-4.250 -0.0481 0.00983 0.00385 -0.1022 0.9230 0.0089
-4.000 -0.0204 0.00932 0.00318 -0.1022 0.9180 0.0117
-3.750 0.0082 0.00891 0.00276 -0.1023 0.9137 0.0194
-3.500 0.0352 0.00879 0.00261 -0.1022 0.9078 0.0309
-3.250 0.0632 0.00870 0.00249 -0.1022 0.9026 0.0365
-3.000 0.0908 0.00856 0.00231 -0.1022 0.8975 0.0416
-2.750 0.1180 0.00840 0.00211 -0.1021 0.8913 0.0456
-2.500 0.1458 0.00823 0.00184 -0.1021 0.8859 0.0478
-2.250 0.1726 0.00810 0.00165 -0.1019 0.8791 0.0497
-2.000 0.2001 0.00793 0.00143 -0.1018 0.8727 0.0550
-1.750 0.2269 0.00780 0.00128 -0.1015 0.8649 0.0612
-1.500 0.2537 0.00764 0.00115 -0.1013 0.8548 0.0816
-1.250 0.2795 0.00726 0.00104 -0.1011 0.8437 0.1820
-1.000 0.3060 0.00716 0.00102 -0.1008 0.8309 0.2329
-0.750 0.3327 0.00712 0.00098 -0.1005 0.8187 0.2541
-0.500 0.3595 0.00710 0.00097 -0.1003 0.8070 0.2734
-0.250 0.3862 0.00708 0.00095 -0.1001 0.7943 0.2889
0.000 0.4127 0.00706 0.00093 -0.0998 0.7796 0.3032
0.250 0.4388 0.00706 0.00091 -0.0994 0.7606 0.3186
0.500 0.4647 0.00703 0.00090 -0.0990 0.7403 0.3407
0.750 0.4902 0.00697 0.00093 -0.0986 0.7203 0.3827
1.000 0.5130 0.00648 0.00104 -0.0978 0.7010 0.6289
1.250 0.5347 0.00620 0.00114 -0.0965 0.6825 0.7798
1.750 0.5982 0.00607 0.00130 -0.0981 0.6498 1.0000
2.000 0.6229 0.00628 0.00141 -0.0974 0.6246 1.0000
2.250 0.6473 0.00651 0.00154 -0.0967 0.5969 1.0000
2.500 0.6707 0.00681 0.00171 -0.0958 0.5543 1.0000
2.750 0.6916 0.00731 0.00189 -0.0945 0.4775 1.0000
3.000 0.7049 0.00867 0.00236 -0.0922 0.2866 1.0000
3.250 0.7191 0.01023 0.00306 -0.0902 0.0865 1.0000
3.500 0.7403 0.01100 0.00351 -0.0891 0.0173 1.0000
3.750 0.7649 0.01137 0.00393 -0.0885 0.0124 1.0000
4.000 0.7884 0.01189 0.00455 -0.0876 0.0089 1.0000
4.250 0.8120 0.01238 0.00512 -0.0867 0.0078 1.0000
4.500 0.8346 0.01298 0.00580 -0.0857 0.0069 1.0000
4.750 0.8565 0.01365 0.00651 -0.0847 0.0060 1.0000
5.000 0.8768 0.01451 0.00748 -0.0833 0.0052 1.0000
5.250 0.8975 0.01537 0.00844 -0.0820 0.0047 1.0000
5.500 0.9178 0.01639 0.00956 -0.0805 0.0043 1.0000
5.750 0.9384 0.01750 0.01077 -0.0792 0.0039 1.0000
6.000 0.9595 0.01878 0.01217 -0.0779 0.0037 1.0000
6.250 0.9813 0.02033 0.01387 -0.0767 0.0036 1.0000
6.500 1.0037 0.02232 0.01607 -0.0756 0.0035 1.0000
6.750 1.0258 0.02492 0.01901 -0.0742 0.0035 1.0000
7.000 1.0451 0.02730 0.02165 -0.0728 0.0034 1.0000
7.250 1.0632 0.03118 0.02602 -0.0704 0.0030 1.0000
7.500 1.0781 0.03582 0.03110 -0.0675 0.0027 1.0000
7.750 1.0884 0.04045 0.03614 -0.0644 0.0026 1.0000
8.000 1.0953 0.04497 0.04102 -0.0612 0.0025 1.0000
8.250 1.0989 0.04969 0.04606 -0.0580 0.0025 1.0000
8.500 1.0994 0.05431 0.05096 -0.0549 0.0025 1.0000
8.750 1.0960 0.05884 0.05574 -0.0518 0.0026 1.0000
9.000 1.0895 0.06302 0.06014 -0.0489 0.0026 1.0000
9.250 1.0780 0.06698 0.06428 -0.0458 0.0027 1.0000
9.500 1.0604 0.07034 0.06777 -0.0423 0.0027 1.0000
9.750 1.0423 0.07383 0.07139 -0.0401 0.0027 1.0000
10.000 1.0226 0.07804 0.07571 -0.0394 0.0027 1.0000
10.250 1.0039 0.08273 0.08051 -0.0403 0.0028 1.0000
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Polar data table (+)
Polar graphs
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