GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 564 AIRFOIL (goe564-il) Reynolds number: 50,000 Max Cl/Cd: 37.13 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe564-il-50000.txt Download as CSV file: xf-goe564-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 564 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4543 0.11508 0.10785 -0.0224 1.0000 0.1997
-9.000 -0.4273 0.10885 0.10155 -0.0201 1.0000 0.2116
-8.750 -0.4546 0.10919 0.10209 -0.0218 1.0000 0.2148
-8.500 -0.4259 0.10305 0.09586 -0.0195 1.0000 0.2266
-8.250 -0.4322 0.10047 0.09340 -0.0195 1.0000 0.2324
-8.000 -0.4331 0.09806 0.09106 -0.0186 1.0000 0.2431
-7.750 -0.4245 0.09441 0.08744 -0.0171 1.0000 0.2542
-7.500 -0.4295 0.09191 0.08504 -0.0159 1.0000 0.2649
-7.250 -0.4517 0.09110 0.08441 -0.0144 1.0000 0.2743
-7.000 -0.4533 0.08840 0.08179 -0.0127 1.0000 0.2894
-6.750 -0.4564 0.08585 0.07933 -0.0109 1.0000 0.3047
-6.500 -0.4632 0.08360 0.07717 -0.0094 1.0000 0.3204
-6.250 -0.4471 0.07960 0.07319 -0.0056 1.0000 0.3394
-6.000 -0.4442 0.07703 0.07068 -0.0027 1.0000 0.3608
-5.750 -0.4519 0.07486 0.06861 0.0001 1.0000 0.3834
-5.500 -0.4405 0.07211 0.06587 0.0050 1.0000 0.4181
-5.250 -0.4516 0.07077 0.06464 0.0098 1.0000 0.4561
-5.000 -0.4234 0.06742 0.06126 0.0161 1.0000 0.5125
-4.250 -0.3891 0.04497 0.03713 -0.0304 1.0000 0.1937
-4.000 -0.3623 0.03993 0.03109 -0.0327 1.0000 0.1707
-3.750 -0.3401 0.03720 0.02780 -0.0324 1.0000 0.1694
-3.500 -0.3206 0.03483 0.02539 -0.0316 1.0000 0.1745
-3.250 -0.2971 0.03250 0.02261 -0.0311 1.0000 0.1754
-3.000 -0.2731 0.03049 0.02019 -0.0304 1.0000 0.1783
-2.750 -0.2488 0.02878 0.01802 -0.0298 1.0000 0.1867
-2.500 -0.2250 0.02746 0.01640 -0.0290 1.0000 0.2000
-2.250 -0.2005 0.02603 0.01479 -0.0282 1.0000 0.2149
-2.000 -0.1768 0.02477 0.01359 -0.0275 1.0000 0.2415
-1.750 -0.1536 0.02377 0.01257 -0.0265 1.0000 0.2757
-1.500 -0.1283 0.02290 0.01181 -0.0261 1.0000 0.3184
-1.250 -0.1030 0.02207 0.01117 -0.0256 1.0000 0.3656
-1.000 -0.0788 0.02104 0.01069 -0.0249 1.0000 0.4387
-0.750 -0.0352 0.01897 0.00994 -0.0264 1.0000 1.0000
-0.500 -0.0152 0.01925 0.00982 -0.0254 1.0000 1.0000
-0.250 0.0041 0.01957 0.00985 -0.0244 1.0000 1.0000
0.000 0.0230 0.01993 0.00998 -0.0235 1.0000 1.0000
0.250 0.0416 0.02033 0.01017 -0.0226 1.0000 1.0000
0.500 0.0598 0.02077 0.01045 -0.0218 1.0000 1.0000
0.750 0.0778 0.02125 0.01080 -0.0210 1.0000 1.0000
1.000 0.0956 0.02178 0.01121 -0.0203 1.0000 1.0000
1.250 0.1132 0.02235 0.01169 -0.0196 1.0000 1.0000
1.500 0.1305 0.02297 0.01222 -0.0190 1.0000 1.0000
1.750 0.1477 0.02363 0.01282 -0.0185 1.0000 1.0000
2.000 0.1647 0.02433 0.01348 -0.0180 1.0000 1.0000
2.250 0.1815 0.02509 0.01420 -0.0176 1.0000 1.0000
2.500 0.1979 0.02590 0.01500 -0.0172 1.0000 1.0000
2.750 0.2515 0.02757 0.01671 -0.0239 0.9836 1.0000
3.000 0.3276 0.02892 0.01816 -0.0339 0.9481 1.0000
3.250 0.3947 0.02967 0.01904 -0.0412 0.9177 1.0000
3.500 0.4476 0.03009 0.01964 -0.0457 0.8914 1.0000
3.750 0.5017 0.03020 0.01995 -0.0498 0.8650 1.0000
4.000 0.5592 0.02990 0.01990 -0.0537 0.8379 1.0000
4.250 0.6198 0.02899 0.01933 -0.0572 0.8081 1.0000
4.500 0.6841 0.02736 0.01807 -0.0600 0.7740 1.0000
4.750 0.7451 0.02523 0.01630 -0.0611 0.7304 1.0000
5.000 0.8028 0.02300 0.01417 -0.0607 0.6671 1.0000
5.250 0.8385 0.02259 0.01346 -0.0585 0.5888 1.0000
5.500 0.8596 0.02315 0.01370 -0.0556 0.5243 1.0000
5.750 0.8817 0.02390 0.01420 -0.0536 0.4762 1.0000
6.000 0.9054 0.02493 0.01508 -0.0522 0.4384 1.0000
6.250 0.9293 0.02611 0.01617 -0.0509 0.4044 1.0000
6.500 0.9529 0.02742 0.01733 -0.0497 0.3717 1.0000
6.750 0.9756 0.02895 0.01878 -0.0483 0.3403 1.0000
7.000 0.9905 0.03021 0.02002 -0.0459 0.3043 1.0000
7.250 1.0057 0.03139 0.02092 -0.0436 0.2669 1.0000
7.500 1.0196 0.03313 0.02272 -0.0410 0.2319 1.0000
7.750 1.0361 0.03529 0.02456 -0.0390 0.1945 1.0000
8.000 1.0502 0.03745 0.02670 -0.0365 0.1657 1.0000
8.250 1.0643 0.04002 0.02961 -0.0341 0.1479 1.0000
8.500 1.0794 0.04239 0.03215 -0.0320 0.1344 1.0000
8.750 1.0983 0.04494 0.03478 -0.0307 0.1246 1.0000
9.000 1.1035 0.04864 0.03915 -0.0276 0.1199 1.0000
9.250 1.1176 0.05120 0.04183 -0.0259 0.1128 1.0000
9.500 1.1205 0.05498 0.04599 -0.0233 0.1096 1.0000
9.750 1.1146 0.05929 0.05082 -0.0201 0.1085 1.0000
10.000 1.1057 0.06372 0.05567 -0.0172 0.1083 1.0000
10.250 1.0919 0.06829 0.06057 -0.0144 0.1086 1.0000
10.500 1.0745 0.07283 0.06536 -0.0119 0.1091 1.0000
10.750 1.0548 0.07718 0.06987 -0.0095 0.1098 1.0000
11.000 1.0354 0.08190 0.07471 -0.0081 0.1105 1.0000
11.250 1.0210 0.08705 0.07993 -0.0078 0.1111 1.0000
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Polar data table (+)
Polar graphs
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