GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 564 AIRFOIL (goe564-il) Reynolds number: 200,000 Max Cl/Cd: 75.37 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe564-il-200000.txt Download as CSV file: xf-goe564-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4351 0.10181 0.09807 -0.0287 1.0000 0.0552
-9.250 -0.4528 0.09870 0.09506 -0.0341 1.0000 0.0567
-9.000 -0.4661 0.09549 0.09194 -0.0371 1.0000 0.0570
-8.750 -0.4549 0.09058 0.08702 -0.0333 1.0000 0.0584
-8.500 -0.4452 0.08834 0.08479 -0.0310 1.0000 0.0598
-8.250 -0.4454 0.08585 0.08233 -0.0302 1.0000 0.0611
-8.000 -0.4515 0.08335 0.07989 -0.0295 1.0000 0.0625
-7.750 -0.4644 0.08100 0.07762 -0.0284 1.0000 0.0638
-7.500 -0.4745 0.07790 0.07458 -0.0289 1.0000 0.0651
-7.000 -0.5060 0.06871 0.06507 -0.0385 1.0000 0.0690
-6.750 -0.5069 0.06341 0.05991 -0.0364 1.0000 0.0701
-6.500 -0.5014 0.06142 0.05798 -0.0336 1.0000 0.0711
-6.250 -0.4959 0.05950 0.05607 -0.0315 1.0000 0.0727
-6.000 -0.4898 0.05718 0.05370 -0.0304 1.0000 0.0760
-5.750 -0.4865 0.05064 0.04659 -0.0339 1.0000 0.0829
-5.500 -0.4809 0.03694 0.03215 -0.0341 1.0000 0.0555
-5.250 -0.4680 0.03198 0.02677 -0.0333 1.0000 0.0533
-5.000 -0.4509 0.02782 0.02202 -0.0323 1.0000 0.0540
-4.750 -0.4309 0.02483 0.01845 -0.0312 1.0000 0.0550
-4.500 -0.4095 0.02267 0.01580 -0.0301 1.0000 0.0559
-4.250 -0.3770 0.02069 0.01338 -0.0312 0.9974 0.0582
-4.000 -0.3426 0.01966 0.01227 -0.0329 0.9945 0.0610
-3.750 -0.3094 0.01878 0.01121 -0.0340 0.9910 0.0635
-3.500 -0.2745 0.01816 0.01039 -0.0354 0.9872 0.0675
-3.250 -0.2384 0.01726 0.00938 -0.0371 0.9843 0.0711
-3.000 -0.2064 0.01675 0.00890 -0.0381 0.9798 0.0755
-2.750 -0.1720 0.01632 0.00837 -0.0393 0.9753 0.0825
-2.500 -0.1335 0.01602 0.00810 -0.0416 0.9718 0.0953
-2.250 -0.1032 0.01550 0.00772 -0.0422 0.9663 0.1171
-2.000 -0.0679 0.01526 0.00748 -0.0438 0.9612 0.1414
-1.750 -0.0279 0.01504 0.00734 -0.0465 0.9578 0.1605
-1.500 0.0009 0.01480 0.00716 -0.0468 0.9505 0.1764
-1.250 0.0389 0.01454 0.00697 -0.0490 0.9458 0.1984
-1.000 0.0745 0.01418 0.00680 -0.0507 0.9406 0.2307
-0.750 0.1037 0.01329 0.00664 -0.0513 0.9335 0.3791
-0.500 0.1927 0.01170 0.00675 -0.0633 0.9396 1.0000
-0.250 0.2385 0.01148 0.00641 -0.0666 0.9322 1.0000
0.000 0.2866 0.01114 0.00598 -0.0702 0.9246 1.0000
0.250 0.3351 0.01079 0.00557 -0.0740 0.9180 1.0000
0.500 0.3781 0.01045 0.00520 -0.0766 0.9102 1.0000
0.750 0.4213 0.01006 0.00477 -0.0791 0.9018 1.0000
1.000 0.4549 0.00979 0.00447 -0.0797 0.8894 1.0000
1.250 0.4875 0.00956 0.00423 -0.0801 0.8766 1.0000
1.500 0.5192 0.00937 0.00401 -0.0803 0.8618 1.0000
1.750 0.5490 0.00924 0.00385 -0.0801 0.8458 1.0000
2.000 0.5781 0.00915 0.00372 -0.0798 0.8283 1.0000
2.250 0.6038 0.00914 0.00369 -0.0789 0.8092 1.0000
2.500 0.6283 0.00916 0.00368 -0.0778 0.7882 1.0000
2.750 0.6523 0.00919 0.00367 -0.0765 0.7636 1.0000
3.000 0.6749 0.00925 0.00367 -0.0750 0.7326 1.0000
3.250 0.6977 0.00935 0.00366 -0.0735 0.6969 1.0000
3.500 0.7198 0.00955 0.00369 -0.0718 0.6595 1.0000
3.750 0.7406 0.00987 0.00382 -0.0700 0.6202 1.0000
4.000 0.7597 0.01024 0.00401 -0.0680 0.5757 1.0000
4.250 0.7763 0.01065 0.00421 -0.0654 0.5121 1.0000
4.500 0.7885 0.01132 0.00444 -0.0622 0.4269 1.0000
4.750 0.8020 0.01209 0.00482 -0.0594 0.3578 1.0000
5.000 0.8187 0.01276 0.00524 -0.0573 0.3138 1.0000
5.250 0.8376 0.01333 0.00566 -0.0557 0.2859 1.0000
5.500 0.8575 0.01387 0.00608 -0.0542 0.2641 1.0000
5.750 0.8780 0.01436 0.00651 -0.0529 0.2449 1.0000
6.000 0.8988 0.01483 0.00697 -0.0517 0.2284 1.0000
6.250 0.9195 0.01531 0.00742 -0.0504 0.2121 1.0000
6.500 0.9398 0.01578 0.00785 -0.0491 0.1940 1.0000
6.750 0.9614 0.01613 0.00825 -0.0480 0.1742 1.0000
7.000 0.9819 0.01656 0.00866 -0.0467 0.1521 1.0000
7.250 1.0026 0.01703 0.00905 -0.0455 0.1174 1.0000
7.500 1.0154 0.01832 0.01003 -0.0431 0.0779 1.0000
7.750 1.0285 0.01960 0.01119 -0.0407 0.0604 1.0000
8.000 1.0467 0.02038 0.01200 -0.0389 0.0517 1.0000
8.250 1.0621 0.02139 0.01305 -0.0368 0.0461 1.0000
8.500 1.0770 0.02243 0.01413 -0.0348 0.0425 1.0000
8.750 1.0885 0.02416 0.01583 -0.0322 0.0399 1.0000
9.000 1.1058 0.02531 0.01713 -0.0305 0.0379 1.0000
9.250 1.1222 0.02652 0.01843 -0.0288 0.0352 1.0000
9.500 1.1387 0.02802 0.01997 -0.0273 0.0334 1.0000
9.750 1.1590 0.03079 0.02283 -0.0266 0.0319 1.0000
10.000 1.1782 0.03345 0.02573 -0.0256 0.0311 1.0000
10.250 1.1919 0.03516 0.02773 -0.0236 0.0303 1.0000
10.500 1.2031 0.03707 0.02993 -0.0213 0.0294 1.0000
10.750 1.2113 0.03888 0.03199 -0.0188 0.0282 1.0000
11.000 1.2159 0.04131 0.03471 -0.0160 0.0278 1.0000
11.250 1.2153 0.04384 0.03753 -0.0126 0.0275 1.0000
11.500 1.2098 0.04657 0.04056 -0.0090 0.0274 1.0000
11.750 1.1994 0.04958 0.04388 -0.0054 0.0275 1.0000
12.000 1.1844 0.05292 0.04752 -0.0020 0.0276 1.0000
12.250 1.1664 0.05661 0.05150 0.0005 0.0278 1.0000
12.500 1.1460 0.06072 0.05587 0.0021 0.0279 1.0000
12.750 1.1232 0.06555 0.06096 0.0025 0.0284 1.0000
13.000 1.0985 0.07107 0.06671 0.0014 0.0286 1.0000
13.250 1.0740 0.07734 0.07317 -0.0011 0.0290 1.0000
13.500 1.0469 0.08487 0.08089 -0.0053 0.0292 1.0000
13.750 1.0180 0.09395 0.09013 -0.0114 0.0296 1.0000
14.000 0.9870 0.10510 0.10141 -0.0191 0.0302 1.0000
14.250 0.9560 0.11763 0.11400 -0.0270 0.0309 1.0000
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Polar data table (+)
Polar graphs
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