GOE 590 AIRFOIL (goe590-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 590 AIRFOIL (goe590-il) Reynolds number: 500,000 Max Cl/Cd: 93.91 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe590-il-500000-n5.txt Download as CSV file: xf-goe590-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 590 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3809 0.08934 0.08724 -0.0139 1.0000 0.0064
-7.250 -0.3803 0.08653 0.08447 -0.0147 1.0000 0.0064
-7.000 -0.3783 0.08349 0.08146 -0.0161 1.0000 0.0061
-6.500 -0.3315 0.07322 0.07111 -0.0302 0.9454 0.0033
-6.250 -0.2964 0.06692 0.06462 -0.0400 0.8918 0.0031
-6.000 -0.2828 0.06322 0.06071 -0.0424 0.8420 0.0030
-5.750 -0.2699 0.05980 0.05709 -0.0439 0.8019 0.0030
-5.500 -0.2548 0.05610 0.05321 -0.0456 0.7738 0.0029
-5.250 -0.2373 0.05237 0.04930 -0.0472 0.7536 0.0029
-5.000 -0.2180 0.04852 0.04524 -0.0487 0.7382 0.0028
-4.750 -0.1969 0.04405 0.04058 -0.0501 0.7249 0.0028
-4.500 -0.1748 0.03999 0.03632 -0.0510 0.7129 0.0028
-4.250 -0.1517 0.03484 0.03089 -0.0515 0.7027 0.0029
-4.000 -0.1286 0.02923 0.02491 -0.0512 0.6936 0.0031
-3.750 -0.1066 0.02241 0.01751 -0.0497 0.6849 0.0034
-3.500 -0.0806 0.02324 0.01836 -0.0500 0.6712 0.0041
-3.250 -0.0562 0.01960 0.01430 -0.0488 0.6596 0.0082
-2.750 -0.0045 0.02098 0.01560 -0.0492 0.6274 0.0166
-2.500 0.0202 0.01843 0.01266 -0.0481 0.6133 0.0170
-2.250 0.0446 0.01573 0.00947 -0.0469 0.5992 0.0159
-2.000 0.0699 0.01373 0.00700 -0.0460 0.5849 0.0151
-1.750 0.0959 0.01236 0.00527 -0.0453 0.5720 0.0145
-1.500 0.1218 0.01136 0.00399 -0.0447 0.5606 0.0142
-1.250 0.1474 0.01062 0.00307 -0.0440 0.5514 0.0141
-1.000 0.1726 0.01008 0.00233 -0.0434 0.5435 0.0142
-0.750 0.1982 0.00972 0.00187 -0.0428 0.5359 0.0150
-0.500 0.2241 0.00954 0.00160 -0.0424 0.5291 0.0174
-0.250 0.2506 0.00948 0.00150 -0.0422 0.5225 0.0188
0.000 0.2765 0.00934 0.00129 -0.0418 0.5171 0.0216
0.250 0.3030 0.00925 0.00119 -0.0416 0.5120 0.0242
0.500 0.3292 0.00917 0.00112 -0.0413 0.5071 0.0332
0.750 0.3551 0.00904 0.00110 -0.0410 0.5027 0.0747
1.000 0.3813 0.00895 0.00111 -0.0408 0.4979 0.1133
1.250 0.4075 0.00889 0.00114 -0.0405 0.4933 0.1525
1.500 0.4332 0.00879 0.00118 -0.0403 0.4895 0.2242
1.750 0.4888 0.00708 0.00137 -0.0469 0.4849 0.9792
2.000 0.5521 0.00717 0.00141 -0.0551 0.4797 1.0000
2.250 0.5769 0.00726 0.00147 -0.0546 0.4760 1.0000
2.500 0.6021 0.00732 0.00153 -0.0541 0.4723 1.0000
2.750 0.6271 0.00739 0.00161 -0.0536 0.4686 1.0000
3.000 0.6518 0.00749 0.00175 -0.0530 0.4596 1.0000
3.250 0.6764 0.00759 0.00183 -0.0525 0.4492 1.0000
3.500 0.7014 0.00766 0.00193 -0.0520 0.4400 1.0000
3.750 0.7258 0.00778 0.00203 -0.0514 0.4244 1.0000
4.000 0.7494 0.00798 0.00213 -0.0507 0.3902 1.0000
4.250 0.7524 0.01080 0.00328 -0.0474 0.0370 1.0000
4.500 0.7750 0.01118 0.00359 -0.0466 0.0190 1.0000
4.750 0.7971 0.01164 0.00403 -0.0456 0.0047 1.0000
5.000 0.8199 0.01201 0.00447 -0.0447 0.0042 1.0000
5.250 0.8421 0.01246 0.00514 -0.0436 0.0040 1.0000
5.500 0.8635 0.01298 0.00577 -0.0425 0.0039 1.0000
5.750 0.8837 0.01365 0.00655 -0.0412 0.0039 1.0000
6.000 0.9023 0.01447 0.00751 -0.0396 0.0039 1.0000
6.250 0.9193 0.01544 0.00860 -0.0377 0.0039 1.0000
6.500 0.9346 0.01657 0.00986 -0.0356 0.0039 1.0000
6.750 0.9499 0.01775 0.01116 -0.0335 0.0039 1.0000
7.000 0.9662 0.01890 0.01242 -0.0316 0.0035 1.0000
7.250 0.9851 0.01966 0.01326 -0.0303 0.0028 1.0000
7.500 1.0022 0.02079 0.01452 -0.0288 0.0024 1.0000
7.750 1.0185 0.02233 0.01621 -0.0270 0.0023 1.0000
8.000 1.0343 0.02405 0.01811 -0.0253 0.0019 1.0000
8.250 1.0416 0.02995 0.02461 -0.0220 0.0015 1.0000
8.500 1.0496 0.03455 0.02966 -0.0191 0.0014 1.0000
8.750 1.0589 0.03795 0.03335 -0.0167 0.0014 1.0000
9.000 1.0643 0.04169 0.03738 -0.0142 0.0013 1.0000
9.250 1.0642 0.04577 0.04174 -0.0113 0.0013 1.0000
9.500 1.0584 0.04965 0.04588 -0.0084 0.0014 1.0000
9.750 1.0501 0.05312 0.04955 -0.0052 0.0013 1.0000
10.000 1.0242 0.05661 0.05325 -0.0016 0.0014 1.0000
10.250 1.0188 0.05959 0.05635 -0.0001 0.0014 1.0000
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Polar data table (+)
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