GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 500,000 Max Cl/Cd: 96.45 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe488-il-500000.txt Download as CSV file: xf-goe488-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4100 0.09642 0.09408 -0.0257 1.0000 0.0251
-8.750 -0.4146 0.09336 0.09106 -0.0286 1.0000 0.0256
-8.500 -0.4166 0.09036 0.08809 -0.0292 1.0000 0.0257
-8.250 -0.3588 0.07302 0.07095 -0.0317 1.0000 0.0262
-8.000 -0.3666 0.07021 0.06818 -0.0295 1.0000 0.0265
-7.750 -0.3779 0.06860 0.06662 -0.0264 1.0000 0.0268
-7.500 -0.3951 0.06723 0.06530 -0.0232 0.9997 0.0269
-7.250 -0.3810 0.06344 0.06150 -0.0265 0.9969 0.0274
-7.000 -0.4475 0.06971 0.06759 -0.0318 0.9971 0.0268
-6.750 -0.4246 0.06694 0.06480 -0.0348 0.9949 0.0276
-6.500 -0.4004 0.06356 0.06137 -0.0391 0.9920 0.0289
-6.250 -0.3587 0.05781 0.05544 -0.0497 0.9877 0.0335
-6.000 -0.3245 0.05163 0.04904 -0.0568 0.9848 0.0338
-5.750 -0.3087 0.04218 0.03937 -0.0624 0.9798 0.0352
-5.500 -0.2812 0.04045 0.03758 -0.0643 0.9761 0.0361
-5.250 -0.2493 0.03850 0.03555 -0.0671 0.9735 0.0381
-5.000 -0.2052 0.03534 0.03196 -0.0708 0.9714 0.0440
-4.750 -0.1560 0.01228 0.00873 -0.0753 0.9617 0.0465
-4.500 -0.1265 0.01096 0.00736 -0.0767 0.9592 0.0481
-4.250 -0.0958 0.00961 0.00588 -0.0782 0.9569 0.0515
-4.000 -0.0660 0.01000 0.00592 -0.0774 0.9511 0.0565
-3.750 -0.0583 0.01763 0.01258 -0.0781 0.9561 0.0429
-3.500 -0.0362 0.01572 0.01039 -0.0770 0.9495 0.0420
-3.250 -0.0054 0.01440 0.00884 -0.0774 0.9459 0.0422
-3.000 0.0270 0.01314 0.00740 -0.0782 0.9430 0.0420
-2.750 0.0538 0.01235 0.00649 -0.0778 0.9373 0.0423
-2.500 0.0824 0.01164 0.00568 -0.0777 0.9321 0.0427
-2.250 0.1128 0.01101 0.00499 -0.0780 0.9281 0.0430
-2.000 0.1383 0.01052 0.00446 -0.0773 0.9211 0.0434
-1.750 0.1667 0.01014 0.00404 -0.0771 0.9149 0.0440
-1.500 0.1922 0.00956 0.00342 -0.0764 0.9074 0.0451
-1.250 0.2185 0.00903 0.00286 -0.0758 0.9002 0.0465
-1.000 0.2440 0.00870 0.00252 -0.0751 0.8915 0.0486
-0.750 0.2715 0.00846 0.00226 -0.0747 0.8836 0.0510
-0.500 0.2967 0.00828 0.00208 -0.0739 0.8743 0.0539
-0.250 0.3235 0.00812 0.00188 -0.0734 0.8657 0.0580
0.000 0.3492 0.00782 0.00170 -0.0727 0.8560 0.0905
0.250 0.3729 0.00738 0.00173 -0.0719 0.8455 0.2448
0.500 0.3978 0.00711 0.00168 -0.0712 0.8347 0.3297
0.750 0.4374 0.00554 0.00182 -0.0735 0.8226 0.9694
1.000 0.5142 0.00559 0.00174 -0.0840 0.7980 1.0000
1.250 0.5362 0.00564 0.00169 -0.0825 0.7713 1.0000
1.500 0.5565 0.00577 0.00162 -0.0806 0.7247 1.0000
1.750 0.5714 0.00617 0.00159 -0.0776 0.6377 1.0000
2.000 0.5882 0.00661 0.00169 -0.0752 0.5689 1.0000
2.250 0.6051 0.00708 0.00181 -0.0729 0.4900 1.0000
2.500 0.6229 0.00757 0.00196 -0.0709 0.4245 1.0000
2.750 0.6436 0.00790 0.00211 -0.0694 0.3910 1.0000
3.000 0.6656 0.00817 0.00227 -0.0682 0.3702 1.0000
3.250 0.6881 0.00840 0.00242 -0.0671 0.3535 1.0000
3.500 0.7110 0.00862 0.00257 -0.0661 0.3399 1.0000
3.750 0.7340 0.00883 0.00274 -0.0650 0.3283 1.0000
4.000 0.7571 0.00904 0.00289 -0.0641 0.3150 1.0000
4.250 0.7806 0.00923 0.00305 -0.0631 0.3017 1.0000
4.500 0.8042 0.00941 0.00320 -0.0623 0.2879 1.0000
4.750 0.8276 0.00962 0.00337 -0.0614 0.2718 1.0000
5.000 0.8512 0.00983 0.00353 -0.0605 0.2522 1.0000
5.250 0.8740 0.01011 0.00370 -0.0595 0.2246 1.0000
5.500 0.8953 0.01054 0.00393 -0.0584 0.1849 1.0000
5.750 0.9163 0.01103 0.00427 -0.0572 0.1523 1.0000
6.000 0.9373 0.01154 0.00463 -0.0560 0.1233 1.0000
6.250 0.9557 0.01235 0.00512 -0.0544 0.0680 1.0000
6.500 0.9754 0.01307 0.00569 -0.0530 0.0427 1.0000
6.750 0.9955 0.01376 0.00623 -0.0516 0.0228 1.0000
7.000 1.0170 0.01432 0.00683 -0.0504 0.0195 1.0000
7.250 1.0388 0.01483 0.00743 -0.0493 0.0185 1.0000
7.500 1.0596 0.01543 0.00812 -0.0480 0.0175 1.0000
7.750 1.0792 0.01614 0.00891 -0.0465 0.0164 1.0000
8.000 1.0961 0.01710 0.00995 -0.0447 0.0152 1.0000
8.250 1.1090 0.01842 0.01141 -0.0422 0.0145 1.0000
8.500 1.1267 0.01922 0.01228 -0.0405 0.0142 1.0000
8.750 1.1437 0.02009 0.01324 -0.0387 0.0139 1.0000
9.000 1.1594 0.02107 0.01431 -0.0368 0.0136 1.0000
9.250 1.1744 0.02214 0.01548 -0.0348 0.0132 1.0000
9.500 1.1887 0.02333 0.01677 -0.0327 0.0130 1.0000
9.750 1.2025 0.02463 0.01819 -0.0306 0.0127 1.0000
10.000 1.2158 0.02605 0.01973 -0.0285 0.0124 1.0000
10.250 1.2287 0.02746 0.02125 -0.0264 0.0122 1.0000
10.500 1.2401 0.02892 0.02283 -0.0242 0.0120 1.0000
10.750 1.2501 0.03031 0.02429 -0.0218 0.0115 1.0000
11.000 1.2589 0.03195 0.02601 -0.0196 0.0112 1.0000
11.250 1.2665 0.03389 0.02811 -0.0171 0.0111 1.0000
11.500 1.2716 0.03594 0.03036 -0.0145 0.0111 1.0000
11.750 1.2747 0.03825 0.03283 -0.0120 0.0110 1.0000
12.000 1.2740 0.04028 0.03508 -0.0091 0.0111 1.0000
12.250 1.2689 0.04287 0.03795 -0.0061 0.0113 1.0000
12.500 1.2345 0.04875 0.04448 -0.0019 0.0126 1.0000
12.750 1.2268 0.05139 0.04727 -0.0005 0.0123 1.0000
13.000 1.1995 0.05731 0.05351 0.0004 0.0131 1.0000
13.250 1.1787 0.06261 0.05902 0.0000 0.0135 1.0000
13.500 1.1541 0.06913 0.06572 -0.0019 0.0139 1.0000
13.750 1.0431 0.07288 0.06982 -0.0053 0.0129 1.0000
14.000 1.0186 0.08130 0.07841 -0.0096 0.0131 1.0000
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Polar data table (+)
Polar graphs
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