GOE 491 AIRFOIL (goe491-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 491 AIRFOIL (goe491-il) Reynolds number: 50,000 Max Cl/Cd: 34.63 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe491-il-50000.txt Download as CSV file: xf-goe491-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 491 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4980 0.11217 0.10510 0.0022 1.0000 0.1221
-8.500 -0.5028 0.11059 0.10362 -0.0002 1.0000 0.1251
-8.250 -0.5138 0.10994 0.10310 -0.0035 1.0000 0.1262
-8.000 -0.4904 0.10265 0.09578 -0.0006 1.0000 0.1317
-7.750 -0.4904 0.09994 0.09315 -0.0017 1.0000 0.1369
-7.500 -0.4977 0.09882 0.09212 -0.0058 1.0000 0.1398
-7.250 -0.4865 0.09355 0.08690 -0.0042 1.0000 0.1442
-7.000 -0.4813 0.09047 0.08382 -0.0053 1.0000 0.1513
-6.750 -0.4808 0.08805 0.08145 -0.0095 1.0000 0.1556
-6.500 -0.4695 0.08366 0.07709 -0.0074 1.0000 0.1645
-6.000 -0.4576 0.07847 0.07187 -0.0132 1.0000 0.1830
-5.750 -0.4476 0.07436 0.06781 -0.0119 1.0000 0.1958
-5.500 -0.4389 0.07132 0.06476 -0.0130 1.0000 0.2110
-5.250 -0.4300 0.06686 0.06041 -0.0098 1.0000 0.2290
-5.000 -0.4223 0.06378 0.05734 -0.0093 1.0000 0.2550
-4.750 -0.4146 0.06047 0.05409 -0.0074 1.0000 0.2839
-4.500 -0.4089 0.05765 0.05131 -0.0053 1.0000 0.3239
-4.000 -0.4055 0.05089 0.04484 0.0066 1.0000 0.4270
-3.750 -0.4057 0.04777 0.04188 0.0138 1.0000 0.4847
-3.500 -0.4042 0.04500 0.03921 0.0189 1.0000 0.5340
-3.250 -0.4016 0.04192 0.03630 0.0272 1.0000 0.5858
-3.000 -0.3956 0.03919 0.03362 0.0303 1.0000 0.6189
-2.500 -0.1951 0.03275 0.02360 -0.0167 1.0000 0.1816
-2.250 -0.1707 0.03029 0.02077 -0.0157 1.0000 0.1806
-2.000 -0.1451 0.02791 0.01797 -0.0146 1.0000 0.1768
-1.750 -0.1201 0.02603 0.01567 -0.0135 1.0000 0.1853
-1.500 -0.0941 0.02430 0.01363 -0.0125 1.0000 0.1922
-1.250 -0.0686 0.02293 0.01201 -0.0117 1.0000 0.2071
-1.000 -0.0398 0.02167 0.01049 -0.0112 1.0000 0.2146
-0.750 -0.0066 0.02072 0.00925 -0.0115 1.0000 0.2253
-0.500 0.0230 0.01978 0.00832 -0.0116 1.0000 0.2466
-0.250 0.0493 0.01904 0.00757 -0.0110 1.0000 0.2634
0.000 0.0723 0.01833 0.00701 -0.0100 1.0000 0.2885
0.250 0.0942 0.01702 0.00653 -0.0092 1.0000 0.3971
0.500 0.1619 0.01583 0.00579 -0.0157 1.0000 1.0000
0.750 0.1795 0.01608 0.00586 -0.0142 1.0000 1.0000
1.000 0.1961 0.01638 0.00604 -0.0127 1.0000 1.0000
1.250 0.2115 0.01677 0.00636 -0.0112 1.0000 1.0000
1.500 0.2251 0.01728 0.00685 -0.0098 1.0000 1.0000
1.750 0.2360 0.01800 0.00756 -0.0086 1.0000 1.0000
2.000 0.2582 0.01909 0.00868 -0.0108 0.9933 1.0000
2.250 0.3644 0.01993 0.00969 -0.0277 0.9452 1.0000
2.500 0.4662 0.01980 0.00986 -0.0418 0.9004 1.0000
2.750 0.5373 0.01948 0.00975 -0.0486 0.8540 1.0000
3.000 0.5819 0.01935 0.00977 -0.0499 0.8093 1.0000
3.250 0.6130 0.01945 0.00989 -0.0487 0.7689 1.0000
3.500 0.6411 0.01968 0.01010 -0.0471 0.7330 1.0000
3.750 0.6647 0.02016 0.01061 -0.0452 0.6979 1.0000
4.000 0.6889 0.02068 0.01115 -0.0434 0.6655 1.0000
4.250 0.7123 0.02129 0.01184 -0.0414 0.6341 1.0000
4.500 0.7325 0.02188 0.01247 -0.0389 0.5974 1.0000
4.750 0.7518 0.02231 0.01285 -0.0359 0.5571 1.0000
5.000 0.7713 0.02279 0.01329 -0.0331 0.5178 1.0000
5.250 0.7878 0.02303 0.01341 -0.0296 0.4699 1.0000
5.500 0.8015 0.02318 0.01344 -0.0258 0.4139 1.0000
5.750 0.8148 0.02353 0.01372 -0.0223 0.3519 1.0000
6.000 0.8197 0.02476 0.01424 -0.0173 0.2304 1.0000
6.250 0.8384 0.02731 0.01628 -0.0151 0.1768 1.0000
6.500 0.8594 0.02938 0.01826 -0.0136 0.1507 1.0000
6.750 0.8835 0.03181 0.02079 -0.0123 0.1369 1.0000
7.000 0.9063 0.03449 0.02377 -0.0110 0.1271 1.0000
7.250 0.9263 0.03702 0.02643 -0.0097 0.1164 1.0000
7.500 0.9444 0.04040 0.03043 -0.0079 0.1123 1.0000
7.750 0.9600 0.04410 0.03462 -0.0061 0.1097 1.0000
8.000 0.9758 0.04777 0.03836 -0.0049 0.1048 1.0000
8.250 0.9803 0.05193 0.04324 -0.0028 0.1031 1.0000
8.500 0.9825 0.05664 0.04845 -0.0011 0.1030 1.0000
8.750 0.9843 0.06165 0.05381 0.0001 0.1041 1.0000
9.000 0.9842 0.06686 0.05934 0.0010 0.1058 1.0000
9.250 0.9393 0.07398 0.06704 0.0002 0.1111 1.0000
9.500 0.9174 0.07993 0.07308 -0.0009 0.1141 1.0000
9.750 0.9067 0.08536 0.07852 -0.0017 0.1167 1.0000
10.000 0.8662 0.09696 0.09004 -0.0117 0.1298 1.0000
10.250 0.8699 0.10231 0.09538 -0.0121 0.1314 1.0000
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Polar data table (+)
Polar graphs
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