GOE 563 AIRFOIL (goe563-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 563 AIRFOIL (goe563-il) Reynolds number: 100,000 Max Cl/Cd: 54.14 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe563-il-100000.txt Download as CSV file: xf-goe563-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3510 0.09273 0.08778 -0.0291 1.0000 0.1225
-9.000 -0.3631 0.08963 0.08474 -0.0310 1.0000 0.1270
-8.750 -0.3926 0.08700 0.08225 -0.0347 1.0000 0.1285
-8.500 -0.3705 0.08180 0.07703 -0.0317 1.0000 0.1315
-8.250 -0.3618 0.07866 0.07390 -0.0302 1.0000 0.1355
-8.000 -0.3703 0.07555 0.07085 -0.0305 1.0000 0.1400
-7.750 -0.4671 0.08210 0.07724 -0.0292 1.0000 0.1334
-7.500 -0.4697 0.07933 0.07453 -0.0287 1.0000 0.1374
-7.250 -0.5068 0.07608 0.07126 -0.0357 1.0000 0.1433
-7.000 -0.5020 0.07188 0.06714 -0.0334 1.0000 0.1455
-6.750 -0.4913 0.06952 0.06483 -0.0297 1.0000 0.1488
-6.500 -0.5141 0.06641 0.06144 -0.0339 1.0000 0.1591
-6.250 -0.4999 0.06301 0.05825 -0.0298 1.0000 0.1616
-5.750 -0.4925 0.05777 0.05296 -0.0269 1.0000 0.1785
-5.500 -0.4901 0.05481 0.04986 -0.0269 1.0000 0.1913
-5.250 -0.4804 0.05253 0.04759 -0.0247 1.0000 0.1985
-5.000 -0.4590 0.03681 0.02950 -0.0311 1.0000 0.0989
-4.750 -0.4423 0.03411 0.02644 -0.0299 1.0000 0.0989
-4.500 -0.4241 0.03137 0.02340 -0.0288 1.0000 0.0985
-4.250 -0.4045 0.02898 0.02066 -0.0278 1.0000 0.0979
-4.000 -0.3835 0.02709 0.01840 -0.0266 1.0000 0.0981
-3.750 -0.3622 0.02535 0.01636 -0.0257 1.0000 0.1007
-3.500 -0.3410 0.02418 0.01515 -0.0249 1.0000 0.1044
-3.250 -0.3188 0.02307 0.01381 -0.0239 1.0000 0.1068
-3.000 -0.2964 0.02210 0.01263 -0.0229 1.0000 0.1100
-2.750 -0.2741 0.02133 0.01163 -0.0218 1.0000 0.1143
-2.500 -0.2531 0.02046 0.01088 -0.0209 1.0000 0.1225
-2.250 -0.2316 0.01977 0.01012 -0.0199 1.0000 0.1312
-2.000 -0.2104 0.01910 0.00952 -0.0189 1.0000 0.1448
-1.750 -0.1903 0.01847 0.00911 -0.0178 1.0000 0.1679
-1.500 -0.1704 0.01785 0.00873 -0.0168 1.0000 0.2097
-1.250 -0.1501 0.01711 0.00844 -0.0160 1.0000 0.2782
-1.000 -0.0957 0.01499 0.00876 -0.0202 1.0000 1.0000
-0.750 -0.0644 0.01540 0.00890 -0.0216 0.9964 1.0000
-0.500 -0.0213 0.01594 0.00917 -0.0253 0.9883 1.0000
-0.250 0.0218 0.01648 0.00952 -0.0289 0.9803 1.0000
0.000 0.0647 0.01696 0.00984 -0.0325 0.9718 1.0000
0.250 0.1034 0.01734 0.01011 -0.0351 0.9619 1.0000
0.500 0.1494 0.01770 0.01037 -0.0390 0.9508 1.0000
0.750 0.2015 0.01791 0.01049 -0.0437 0.9379 1.0000
1.000 0.2547 0.01799 0.01053 -0.0484 0.9264 1.0000
1.250 0.2926 0.01806 0.01059 -0.0504 0.9138 1.0000
1.500 0.3323 0.01811 0.01063 -0.0525 0.9018 1.0000
1.750 0.3772 0.01804 0.01060 -0.0555 0.8912 1.0000
2.000 0.4302 0.01777 0.01039 -0.0598 0.8822 1.0000
2.250 0.4694 0.01757 0.01025 -0.0614 0.8694 1.0000
2.500 0.5083 0.01730 0.01006 -0.0627 0.8566 1.0000
2.750 0.5473 0.01693 0.00977 -0.0638 0.8433 1.0000
3.000 0.5848 0.01647 0.00940 -0.0644 0.8285 1.0000
3.250 0.6222 0.01579 0.00880 -0.0645 0.8100 1.0000
3.500 0.6539 0.01518 0.00824 -0.0635 0.7864 1.0000
3.750 0.6853 0.01466 0.00774 -0.0624 0.7613 1.0000
4.000 0.7109 0.01445 0.00756 -0.0608 0.7324 1.0000
4.250 0.7350 0.01434 0.00745 -0.0589 0.6980 1.0000
4.500 0.7590 0.01431 0.00735 -0.0571 0.6572 1.0000
4.750 0.7805 0.01446 0.00740 -0.0550 0.6085 1.0000
5.000 0.8008 0.01479 0.00751 -0.0527 0.5538 1.0000
5.250 0.8191 0.01532 0.00777 -0.0504 0.4961 1.0000
5.500 0.8360 0.01599 0.00813 -0.0480 0.4400 1.0000
5.750 0.8521 0.01674 0.00859 -0.0456 0.3889 1.0000
6.000 0.8680 0.01756 0.00912 -0.0435 0.3422 1.0000
6.250 0.8846 0.01838 0.00976 -0.0415 0.3003 1.0000
6.500 0.9015 0.01920 0.01044 -0.0396 0.2626 1.0000
6.750 0.9179 0.02001 0.01113 -0.0377 0.2262 1.0000
7.000 0.9327 0.02097 0.01195 -0.0356 0.1852 1.0000
7.250 0.9439 0.02248 0.01309 -0.0330 0.1401 1.0000
7.500 0.9586 0.02424 0.01463 -0.0309 0.1142 1.0000
7.750 0.9769 0.02579 0.01608 -0.0294 0.0995 1.0000
8.000 0.9986 0.02747 0.01780 -0.0282 0.0898 1.0000
8.250 1.0207 0.02924 0.01950 -0.0275 0.0820 1.0000
8.500 1.0428 0.03081 0.02130 -0.0263 0.0761 1.0000
8.750 1.0681 0.03331 0.02364 -0.0263 0.0710 1.0000
9.000 1.0860 0.03496 0.02574 -0.0245 0.0673 1.0000
9.250 1.1053 0.03721 0.02827 -0.0232 0.0643 1.0000
9.500 1.1229 0.03968 0.03097 -0.0218 0.0622 1.0000
9.750 1.1399 0.04314 0.03454 -0.0210 0.0599 1.0000
10.000 1.1448 0.04608 0.03798 -0.0181 0.0587 1.0000
10.250 1.1458 0.04909 0.04150 -0.0150 0.0577 1.0000
10.500 1.1438 0.05278 0.04561 -0.0120 0.0575 1.0000
10.750 1.1374 0.05662 0.04983 -0.0090 0.0577 1.0000
11.000 1.1265 0.06051 0.05404 -0.0059 0.0580 1.0000
11.250 1.1110 0.06421 0.05799 -0.0026 0.0583 1.0000
11.500 1.0932 0.06811 0.06209 0.0000 0.0587 1.0000
11.750 1.0773 0.07254 0.06668 0.0016 0.0591 1.0000
12.000 1.0659 0.07759 0.07187 0.0021 0.0597 1.0000
12.250 1.0262 0.08167 0.07627 0.0018 0.0607 1.0000
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Polar data table (+)
Polar graphs
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