GOE 590 AIRFOIL (goe590-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 590 AIRFOIL (goe590-il) Reynolds number: 50,000 Max Cl/Cd: 38.37 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe590-il-50000-n5.txt Download as CSV file: xf-goe590-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4015 0.10396 0.09745 -0.0132 1.0000 0.0609
-7.750 -0.4022 0.10225 0.09586 -0.0157 1.0000 0.0620
-7.500 -0.4004 0.10076 0.09444 -0.0198 1.0000 0.0627
-7.250 -0.3946 0.09904 0.09276 -0.0242 1.0000 0.0631
-7.000 -0.3842 0.09151 0.08531 -0.0189 1.0000 0.0667
-6.750 -0.3767 0.08828 0.08212 -0.0199 1.0000 0.0699
-6.500 -0.3689 0.08575 0.07963 -0.0229 1.0000 0.0745
-6.250 -0.3570 0.08476 0.07859 -0.0290 1.0000 0.0766
-6.000 -0.3487 0.07996 0.07388 -0.0285 1.0000 0.0780
-5.750 -0.3405 0.07572 0.06966 -0.0271 1.0000 0.0812
-5.500 -0.3293 0.07262 0.06656 -0.0281 1.0000 0.0853
-5.250 -0.3085 0.07199 0.06570 -0.0337 1.0000 0.0906
-5.000 -0.3017 0.06699 0.06086 -0.0321 1.0000 0.0922
-4.750 -0.2925 0.06345 0.05737 -0.0311 1.0000 0.0953
-4.500 -0.2799 0.06060 0.05449 -0.0312 1.0000 0.0991
-4.000 -0.2562 0.05536 0.04915 -0.0312 1.0000 0.1085
-3.500 -0.1964 0.04775 0.04102 -0.0361 0.9849 0.0693
-3.250 -0.1529 0.04321 0.03604 -0.0404 0.9693 0.0552
-3.000 -0.1049 0.03923 0.03127 -0.0441 0.9549 0.0492
-2.750 -0.0673 0.03554 0.02722 -0.0470 0.9404 0.0512
-2.500 -0.0305 0.03295 0.02427 -0.0493 0.9247 0.0579
-2.250 0.0085 0.03001 0.02070 -0.0510 0.9095 0.0591
-2.000 0.0452 0.02784 0.01804 -0.0524 0.8935 0.0685
-1.750 0.0831 0.02573 0.01525 -0.0535 0.8779 0.0740
-1.500 0.1209 0.02385 0.01280 -0.0546 0.8625 0.0788
-1.250 0.1586 0.02278 0.01139 -0.0560 0.8464 0.0946
-1.000 0.1966 0.02169 0.00987 -0.0571 0.8308 0.1016
-0.750 0.2273 0.02089 0.00877 -0.0570 0.8142 0.1084
-0.500 0.2546 0.02033 0.00798 -0.0564 0.7983 0.1192
-0.250 0.2799 0.01980 0.00738 -0.0557 0.7833 0.1396
0.000 0.3493 0.01686 0.00642 -0.0640 0.7711 1.0000
0.250 0.3740 0.01707 0.00621 -0.0631 0.7570 1.0000
0.500 0.3985 0.01731 0.00613 -0.0623 0.7440 1.0000
0.750 0.4229 0.01756 0.00611 -0.0614 0.7320 1.0000
1.000 0.4469 0.01784 0.00621 -0.0607 0.7200 1.0000
1.250 0.4709 0.01815 0.00637 -0.0600 0.7087 1.0000
1.500 0.4949 0.01846 0.00656 -0.0593 0.6984 1.0000
1.750 0.5195 0.01876 0.00676 -0.0586 0.6895 1.0000
2.000 0.5431 0.01912 0.00713 -0.0581 0.6795 1.0000
2.250 0.5674 0.01949 0.00748 -0.0575 0.6708 1.0000
2.500 0.5923 0.01984 0.00784 -0.0570 0.6628 1.0000
2.750 0.6163 0.02028 0.00840 -0.0566 0.6543 1.0000
3.000 0.6413 0.02064 0.00881 -0.0561 0.6476 1.0000
3.250 0.6647 0.02115 0.00946 -0.0557 0.6393 1.0000
3.500 0.6897 0.02155 0.00996 -0.0552 0.6334 1.0000
3.750 0.7126 0.02214 0.01083 -0.0547 0.6255 1.0000
4.000 0.7374 0.02259 0.01146 -0.0542 0.6198 1.0000
4.250 0.7599 0.02326 0.01241 -0.0537 0.6124 1.0000
4.500 0.7842 0.02379 0.01321 -0.0532 0.6068 1.0000
4.750 0.8067 0.02452 0.01430 -0.0527 0.6002 1.0000
5.000 0.8308 0.02494 0.01513 -0.0517 0.5921 1.0000
5.250 0.8497 0.02354 0.01378 -0.0468 0.5475 1.0000
5.500 0.8575 0.02235 0.01242 -0.0404 0.4600 1.0000
5.750 0.8461 0.02479 0.01272 -0.0346 0.1096 1.0000
6.000 0.8505 0.02781 0.01535 -0.0323 0.0690 1.0000
6.250 0.8586 0.02992 0.01760 -0.0300 0.0556 1.0000
6.500 0.8654 0.03193 0.01975 -0.0277 0.0479 1.0000
6.750 0.8713 0.03393 0.02201 -0.0250 0.0444 1.0000
7.000 0.8805 0.03564 0.02391 -0.0226 0.0403 1.0000
7.250 0.8909 0.03769 0.02594 -0.0202 0.0359 1.0000
7.500 0.9209 0.03944 0.02797 -0.0185 0.0336 1.0000
7.750 0.9587 0.04195 0.03072 -0.0179 0.0312 1.0000
8.000 0.9866 0.04509 0.03394 -0.0176 0.0280 1.0000
8.250 1.0091 0.04876 0.03793 -0.0167 0.0268 1.0000
8.500 1.0261 0.05223 0.04185 -0.0152 0.0266 1.0000
8.750 1.0388 0.05586 0.04590 -0.0136 0.0266 1.0000
9.000 1.0472 0.05967 0.05023 -0.0120 0.0267 1.0000
9.250 1.0521 0.06352 0.05442 -0.0104 0.0269 1.0000
9.500 1.0541 0.06755 0.05876 -0.0088 0.0270 1.0000
9.750 1.0528 0.07168 0.06316 -0.0074 0.0272 1.0000
10.750 0.9938 0.08454 0.07721 -0.0025 0.0287 1.0000
11.000 0.9752 0.08917 0.08203 -0.0043 0.0290 1.0000
11.250 0.9560 0.09456 0.08757 -0.0072 0.0295 1.0000
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Polar data table (+)
Polar graphs
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