GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 368 AIRFOIL (goe368-il) Reynolds number: 500,000 Max Cl/Cd: 83.61 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe368-il-500000-n5.txt Download as CSV file: xf-goe368-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 368 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3752 0.08702 0.08494 -0.0104 1.0000 0.0050
-7.500 -0.3737 0.08397 0.08192 -0.0113 1.0000 0.0049
-7.250 -0.3764 0.08070 0.07870 -0.0119 1.0000 0.0049
-7.000 -0.3758 0.07751 0.07555 -0.0132 1.0000 0.0047
-6.750 -0.3723 0.07336 0.07142 -0.0162 1.0000 0.0047
-6.500 -0.3657 0.06929 0.06737 -0.0193 1.0000 0.0045
-6.250 -0.3575 0.06461 0.06270 -0.0231 1.0000 0.0044
-6.000 -0.3321 0.05758 0.05563 -0.0321 0.9913 0.0045
-5.750 -0.2975 0.04865 0.04658 -0.0435 0.9792 0.0045
-5.500 -0.2558 0.02755 0.02470 -0.0610 0.9649 0.0043
-5.250 -0.2195 0.02126 0.01760 -0.0655 0.9416 0.0051
-5.000 -0.1774 0.01805 0.01361 -0.0687 0.8860 0.0063
-4.750 -0.1495 0.01789 0.01299 -0.0684 0.8346 0.0068
-4.500 -0.1272 0.01586 0.01066 -0.0680 0.8080 0.0079
-4.250 -0.1021 0.01535 0.00999 -0.0676 0.7858 0.0089
-4.000 -0.0765 0.01447 0.00886 -0.0670 0.7633 0.0097
-3.750 -0.0506 0.01369 0.00783 -0.0664 0.7385 0.0107
-3.500 -0.0247 0.01308 0.00697 -0.0658 0.7094 0.0115
-3.250 0.0014 0.01278 0.00639 -0.0652 0.6810 0.0126
-3.000 0.0275 0.01217 0.00557 -0.0646 0.6580 0.0127
-2.750 0.0538 0.01162 0.00483 -0.0641 0.6394 0.0127
-2.500 0.0802 0.01118 0.00422 -0.0636 0.6206 0.0127
-2.250 0.1068 0.01081 0.00370 -0.0631 0.6003 0.0129
-2.000 0.1334 0.01053 0.00327 -0.0626 0.5773 0.0131
-1.750 0.1603 0.01033 0.00294 -0.0622 0.5537 0.0136
-1.500 0.1872 0.01008 0.00255 -0.0619 0.5301 0.0145
-1.250 0.2140 0.00983 0.00210 -0.0615 0.5016 0.0165
-1.000 0.2405 0.00979 0.00183 -0.0611 0.4691 0.0177
-0.750 0.2671 0.00980 0.00165 -0.0607 0.4423 0.0191
-0.500 0.2939 0.00982 0.00152 -0.0604 0.4205 0.0207
-0.250 0.3208 0.00988 0.00145 -0.0601 0.4025 0.0208
0.000 0.3479 0.00992 0.00140 -0.0598 0.3872 0.0210
0.250 0.3751 0.00997 0.00139 -0.0595 0.3740 0.0218
0.500 0.4023 0.01003 0.00137 -0.0593 0.3616 0.0254
0.750 0.4289 0.00983 0.00137 -0.0591 0.3497 0.1040
1.000 0.4561 0.00988 0.00139 -0.0588 0.3378 0.1134
1.250 0.4831 0.00992 0.00144 -0.0586 0.3259 0.1285
1.500 0.5101 0.00997 0.00151 -0.0584 0.3140 0.1488
1.750 0.5370 0.01005 0.00160 -0.0582 0.3017 0.1649
2.000 0.5639 0.01013 0.00170 -0.0580 0.2888 0.1855
2.500 0.6175 0.01036 0.00191 -0.0575 0.2617 0.2121
2.750 0.6442 0.01049 0.00201 -0.0573 0.2494 0.2195
3.000 0.6710 0.01061 0.00212 -0.0570 0.2383 0.2286
3.250 0.6977 0.01073 0.00228 -0.0568 0.2285 0.2405
3.500 0.7243 0.01084 0.00242 -0.0566 0.2199 0.2608
3.750 0.7501 0.01069 0.00262 -0.0564 0.2121 0.4179
4.000 0.7789 0.00965 0.00281 -0.0567 0.2056 1.0000
4.250 0.8052 0.00984 0.00298 -0.0564 0.1996 1.0000
4.500 0.8315 0.01005 0.00321 -0.0561 0.1948 1.0000
4.750 0.8578 0.01026 0.00340 -0.0557 0.1880 1.0000
5.000 0.8828 0.01064 0.00362 -0.0554 0.1642 1.0000
5.250 0.9085 0.01092 0.00385 -0.0550 0.1543 1.0000
5.500 0.9300 0.01183 0.00433 -0.0543 0.0842 1.0000
5.750 0.9495 0.01319 0.00539 -0.0531 0.0067 1.0000
6.000 0.9746 0.01359 0.00590 -0.0525 0.0055 1.0000
6.250 0.9997 0.01398 0.00637 -0.0520 0.0051 1.0000
6.500 1.0245 0.01439 0.00691 -0.0515 0.0043 1.0000
6.750 1.0487 0.01489 0.00751 -0.0509 0.0037 1.0000
7.000 1.0723 0.01551 0.00824 -0.0502 0.0033 1.0000
7.250 1.0948 0.01626 0.00910 -0.0494 0.0030 1.0000
7.500 1.1164 0.01712 0.01008 -0.0485 0.0027 1.0000
7.750 1.1368 0.01810 0.01119 -0.0474 0.0026 1.0000
8.000 1.1556 0.01922 0.01244 -0.0462 0.0025 1.0000
8.250 1.1728 0.02045 0.01380 -0.0448 0.0024 1.0000
8.500 1.1884 0.02178 0.01525 -0.0432 0.0024 1.0000
8.750 1.2022 0.02321 0.01684 -0.0415 0.0023 1.0000
9.000 1.2151 0.02463 0.01837 -0.0397 0.0023 1.0000
9.250 1.2253 0.02628 0.02012 -0.0376 0.0023 1.0000
9.500 1.2354 0.02783 0.02178 -0.0356 0.0023 1.0000
9.750 1.2432 0.02956 0.02362 -0.0333 0.0024 1.0000
10.000 1.2484 0.03123 0.02539 -0.0307 0.0024 1.0000
10.250 1.2513 0.03309 0.02736 -0.0280 0.0024 1.0000
10.500 1.2550 0.03505 0.02944 -0.0256 0.0025 1.0000
10.750 1.2588 0.03718 0.03169 -0.0237 0.0025 1.0000
11.000 1.2619 0.03961 0.03427 -0.0220 0.0026 1.0000
11.250 1.2638 0.04226 0.03709 -0.0207 0.0027 1.0000
11.500 1.2634 0.04529 0.04031 -0.0197 0.0028 1.0000
11.750 1.2611 0.04849 0.04369 -0.0191 0.0029 1.0000
12.000 1.2575 0.05198 0.04736 -0.0190 0.0030 1.0000
12.250 1.2517 0.05592 0.05149 -0.0195 0.0031 1.0000
12.500 1.2435 0.06035 0.05612 -0.0205 0.0032 1.0000
12.750 1.2342 0.06505 0.06099 -0.0222 0.0032 1.0000
13.000 1.2237 0.07010 0.06621 -0.0244 0.0033 1.0000
13.250 1.2122 0.07560 0.07187 -0.0271 0.0033 1.0000
13.500 1.1998 0.08147 0.07791 -0.0303 0.0034 1.0000
13.750 1.1857 0.08802 0.08462 -0.0341 0.0035 1.0000
14.000 1.1737 0.09434 0.09108 -0.0379 0.0035 1.0000
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Polar data table (+)
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