GOE 563 AIRFOIL (goe563-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 563 AIRFOIL (goe563-il) Reynolds number: 50,000 Max Cl/Cd: 35.87 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe563-il-50000.txt Download as CSV file: xf-goe563-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 563 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4670 0.12417 0.11670 -0.0182 1.0000 0.2045
-10.000 -0.4414 0.11829 0.11072 -0.0165 1.0000 0.2146
-9.750 -0.4675 0.11870 0.11130 -0.0192 1.0000 0.2192
-9.500 -0.4436 0.11312 0.10567 -0.0174 1.0000 0.2328
-9.250 -0.4306 0.10891 0.10146 -0.0166 1.0000 0.2428
-9.000 -0.4407 0.10693 0.09959 -0.0174 1.0000 0.2516
-8.750 -0.4391 0.10444 0.09715 -0.0170 1.0000 0.2639
-8.500 -0.4244 0.10029 0.09300 -0.0158 1.0000 0.2756
-8.250 -0.4205 0.09722 0.08999 -0.0151 1.0000 0.2873
-8.000 -0.4186 0.09448 0.08731 -0.0142 1.0000 0.3013
-7.750 -0.4154 0.09187 0.08474 -0.0128 1.0000 0.3192
-7.500 -0.4194 0.08983 0.08279 -0.0112 1.0000 0.3376
-7.250 -0.4287 0.08814 0.08122 -0.0092 1.0000 0.3544
-7.000 -0.4416 0.08666 0.07987 -0.0065 1.0000 0.3705
-6.750 -0.4052 0.08158 0.07470 -0.0052 1.0000 0.3947
-6.500 -0.4196 0.08035 0.07362 -0.0018 1.0000 0.4152
-6.250 -0.3993 0.07662 0.06988 0.0001 1.0000 0.4397
-6.000 -0.3919 0.07413 0.06744 0.0033 1.0000 0.4710
-5.750 -0.3935 0.07240 0.06578 0.0077 1.0000 0.5070
-5.500 -0.3679 0.06880 0.06215 0.0097 1.0000 0.5460
-5.000 -0.4550 0.04814 0.04035 -0.0310 1.0000 0.1866
-4.750 -0.4393 0.04366 0.03527 -0.0316 1.0000 0.1751
-4.500 -0.4214 0.04061 0.03181 -0.0311 1.0000 0.1719
-4.250 -0.4027 0.03769 0.02857 -0.0304 1.0000 0.1691
-4.000 -0.3822 0.03499 0.02543 -0.0298 1.0000 0.1666
-3.750 -0.3607 0.03275 0.02273 -0.0290 1.0000 0.1671
-3.500 -0.3386 0.03100 0.02047 -0.0281 1.0000 0.1719
-3.250 -0.3166 0.02926 0.01854 -0.0272 1.0000 0.1774
-3.000 -0.2934 0.02778 0.01682 -0.0263 1.0000 0.1829
-2.750 -0.2692 0.02643 0.01516 -0.0255 1.0000 0.1910
-2.500 -0.2459 0.02524 0.01393 -0.0246 1.0000 0.2071
-2.250 -0.2212 0.02403 0.01272 -0.0239 1.0000 0.2280
-2.000 -0.1954 0.02279 0.01158 -0.0232 1.0000 0.2670
-1.750 -0.1715 0.02157 0.01086 -0.0225 1.0000 0.3385
-1.500 -0.1178 0.01836 0.01004 -0.0243 1.0000 1.0000
-1.250 -0.0989 0.01854 0.00974 -0.0232 1.0000 1.0000
-1.000 -0.0804 0.01874 0.00960 -0.0221 1.0000 1.0000
-0.750 -0.0618 0.01898 0.00956 -0.0210 1.0000 1.0000
-0.500 -0.0432 0.01925 0.00957 -0.0200 1.0000 1.0000
-0.250 -0.0246 0.01956 0.00967 -0.0191 1.0000 1.0000
0.000 -0.0060 0.01990 0.00983 -0.0183 1.0000 1.0000
0.250 0.0125 0.02027 0.01005 -0.0175 1.0000 1.0000
0.500 0.0309 0.02069 0.01032 -0.0167 1.0000 1.0000
0.750 0.0492 0.02114 0.01066 -0.0160 1.0000 1.0000
1.000 0.0673 0.02164 0.01106 -0.0154 1.0000 1.0000
1.250 0.0852 0.02218 0.01152 -0.0148 1.0000 1.0000
1.500 0.1028 0.02277 0.01204 -0.0142 1.0000 1.0000
1.750 0.1202 0.02341 0.01263 -0.0138 1.0000 1.0000
2.000 0.1372 0.02410 0.01330 -0.0134 1.0000 1.0000
2.250 0.1538 0.02486 0.01404 -0.0130 1.0000 1.0000
2.500 0.2134 0.02652 0.01573 -0.0208 0.9794 1.0000
2.750 0.2745 0.02799 0.01727 -0.0283 0.9566 1.0000
3.000 0.3248 0.02899 0.01837 -0.0335 0.9321 1.0000
3.250 0.3800 0.02989 0.01940 -0.0391 0.9077 1.0000
3.500 0.4359 0.03046 0.02016 -0.0441 0.8821 1.0000
3.750 0.4846 0.03073 0.02063 -0.0475 0.8544 1.0000
4.000 0.5371 0.03067 0.02083 -0.0508 0.8259 1.0000
4.250 0.5973 0.03000 0.02046 -0.0543 0.7960 1.0000
4.500 0.6664 0.02821 0.01905 -0.0573 0.7638 1.0000
4.750 0.7190 0.02629 0.01738 -0.0570 0.7253 1.0000
5.000 0.7662 0.02460 0.01588 -0.0559 0.6836 1.0000
5.250 0.7999 0.02381 0.01513 -0.0537 0.6356 1.0000
5.500 0.8299 0.02349 0.01469 -0.0513 0.5842 1.0000
5.750 0.8536 0.02380 0.01482 -0.0487 0.5307 1.0000
6.000 0.8766 0.02448 0.01524 -0.0463 0.4781 1.0000
6.250 0.8956 0.02551 0.01604 -0.0438 0.4266 1.0000
6.500 0.9118 0.02650 0.01670 -0.0409 0.3753 1.0000
6.750 0.9250 0.02757 0.01740 -0.0380 0.3259 1.0000
7.000 0.9399 0.02901 0.01865 -0.0356 0.2804 1.0000
7.250 0.9541 0.03076 0.02020 -0.0330 0.2346 1.0000
7.500 0.9703 0.03270 0.02188 -0.0308 0.1957 1.0000
7.750 0.9905 0.03505 0.02427 -0.0292 0.1707 1.0000
8.000 1.0120 0.03728 0.02645 -0.0280 0.1534 1.0000
8.250 1.0316 0.04010 0.02962 -0.0265 0.1425 1.0000
8.500 1.0485 0.04293 0.03269 -0.0249 0.1335 1.0000
8.750 1.0650 0.04590 0.03593 -0.0234 0.1269 1.0000
9.000 1.0788 0.04952 0.03979 -0.0218 0.1227 1.0000
9.250 1.0789 0.05320 0.04411 -0.0188 0.1198 1.0000
9.500 1.0775 0.05701 0.04839 -0.0161 0.1173 1.0000
9.750 1.0725 0.06114 0.05291 -0.0136 0.1161 1.0000
10.000 1.0600 0.06576 0.05791 -0.0110 0.1167 1.0000
10.250 1.0401 0.07053 0.06298 -0.0086 0.1179 1.0000
10.500 1.0148 0.07515 0.06780 -0.0064 0.1193 1.0000
10.750 0.9902 0.08009 0.07286 -0.0053 0.1208 1.0000
11.000 0.9691 0.08562 0.07846 -0.0058 0.1222 1.0000
11.250 0.9579 0.09152 0.08439 -0.0067 0.1234 1.0000
11.500 0.8808 0.10769 0.10055 -0.0192 0.1369 1.0000
11.750 0.7868 0.14206 0.13462 -0.0494 0.2828 1.0000
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Polar data table (+)
Polar graphs
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