GOE 703 AIRFOIL (goe703-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 703 AIRFOIL (goe703-il) Reynolds number: 50,000 Max Cl/Cd: 22.31 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe703-il-50000-n5.txt Download as CSV file: xf-goe703-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 703 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4536 0.10032 0.09188 -0.0640 1.0000 0.0880
-12.750 -0.5405 0.08249 0.07388 -0.0733 1.0000 0.0873
-12.500 -0.6009 0.07336 0.06454 -0.0757 1.0000 0.0866
-12.250 -0.6453 0.06773 0.05872 -0.0746 1.0000 0.0865
-12.000 -0.6802 0.06378 0.05459 -0.0718 1.0000 0.0867
-11.750 -0.7082 0.06077 0.05142 -0.0680 1.0000 0.0869
-11.500 -0.7346 0.05832 0.04879 -0.0634 1.0000 0.0873
-11.250 -0.7588 0.05632 0.04663 -0.0581 1.0000 0.0878
-11.000 -0.7818 0.05469 0.04484 -0.0524 1.0000 0.0882
-10.750 -0.8039 0.05333 0.04331 -0.0462 1.0000 0.0887
-10.500 -0.8201 0.05227 0.04215 -0.0406 1.0000 0.0892
-10.250 -0.8303 0.05146 0.04133 -0.0356 1.0000 0.0899
-10.000 -0.8370 0.05058 0.04041 -0.0312 0.9992 0.0907
-9.750 -0.8094 0.04883 0.03856 -0.0330 0.9905 0.0932
-9.500 -0.7854 0.04695 0.03639 -0.0342 0.9814 0.0966
-9.250 -0.7592 0.04539 0.03471 -0.0353 0.9720 0.1000
-9.000 -0.7295 0.04405 0.03330 -0.0370 0.9634 0.1038
-8.750 -0.6976 0.04240 0.03142 -0.0387 0.9547 0.1090
-8.500 -0.6689 0.04132 0.03038 -0.0399 0.9451 0.1139
-8.250 -0.6336 0.04001 0.02896 -0.0421 0.9374 0.1215
-7.750 -0.5710 0.03790 0.02682 -0.0449 0.9198 0.1408
-7.500 -0.5444 0.03702 0.02596 -0.0454 0.9096 0.1530
-7.250 -0.5111 0.03607 0.02501 -0.0470 0.9020 0.1696
-7.000 -0.4841 0.03532 0.02425 -0.0475 0.8927 0.1866
-6.750 -0.4545 0.03458 0.02349 -0.0484 0.8839 0.2059
-6.500 -0.4145 0.03372 0.02261 -0.0511 0.8786 0.2289
-6.250 -0.3994 0.03339 0.02223 -0.0492 0.8658 0.2458
-6.000 -0.3637 0.03261 0.02154 -0.0511 0.8595 0.2695
-5.750 -0.3459 0.03225 0.02120 -0.0496 0.8482 0.2896
-5.500 -0.3107 0.03152 0.02056 -0.0512 0.8410 0.3147
-5.250 -0.2732 0.03078 0.01989 -0.0532 0.8344 0.3408
-5.000 -0.2515 0.03041 0.01961 -0.0523 0.8237 0.3633
-4.750 -0.2144 0.02963 0.01902 -0.0540 0.8177 0.3957
-4.500 -0.1960 0.02932 0.01891 -0.0524 0.8075 0.4284
-4.250 -0.1649 0.02882 0.01875 -0.0527 0.8000 0.4800
-4.000 -0.0997 0.02865 0.01909 -0.0579 0.7959 0.5713
-3.750 -0.0397 0.02968 0.02031 -0.0614 0.7882 0.6409
-3.500 0.0031 0.03050 0.02105 -0.0624 0.7802 0.6857
-3.250 0.0435 0.03102 0.02138 -0.0633 0.7745 0.7215
-3.000 0.0583 0.03184 0.02212 -0.0603 0.7638 0.7488
-2.750 0.0910 0.03232 0.02244 -0.0602 0.7568 0.7743
-2.500 0.1248 0.03297 0.02295 -0.0604 0.7491 0.7951
-2.250 0.1551 0.03358 0.02344 -0.0603 0.7407 0.8144
-2.000 0.1978 0.03383 0.02352 -0.0623 0.7349 0.8324
-1.750 0.2206 0.03444 0.02405 -0.0613 0.7257 0.8493
-1.500 0.2537 0.03472 0.02421 -0.0620 0.7186 0.8654
-1.250 0.3083 0.03472 0.02403 -0.0664 0.7132 0.8792
-1.000 0.3414 0.03528 0.02456 -0.0674 0.7036 0.8965
-0.750 0.3953 0.03522 0.02438 -0.0719 0.6974 0.9137
-0.500 0.4388 0.03514 0.02422 -0.0751 0.6900 0.9274
-0.250 0.4679 0.03521 0.02424 -0.0759 0.6817 0.9383
0.000 0.5070 0.03481 0.02372 -0.0782 0.6758 0.9459
0.250 0.5297 0.03499 0.02389 -0.0781 0.6671 0.9543
0.500 0.5613 0.03484 0.02368 -0.0794 0.6598 0.9616
0.750 0.5989 0.03443 0.02316 -0.0814 0.6545 0.9679
1.000 0.6193 0.03475 0.02352 -0.0813 0.6449 0.9756
1.250 0.6523 0.03453 0.02325 -0.0827 0.6383 0.9817
1.500 0.6876 0.03422 0.02287 -0.0846 0.6322 0.9873
1.750 0.7093 0.03454 0.02324 -0.0847 0.6230 0.9940
2.000 0.7454 0.03420 0.02285 -0.0867 0.6168 0.9991
2.250 0.7615 0.03449 0.02313 -0.0852 0.6102 1.0000
2.500 0.7653 0.03520 0.02389 -0.0818 0.6017 1.0000
2.750 0.7858 0.03523 0.02387 -0.0807 0.5960 1.0000
3.000 0.7944 0.03580 0.02446 -0.0779 0.5890 1.0000
3.250 0.7958 0.03664 0.02535 -0.0741 0.5807 1.0000
3.500 0.8175 0.03664 0.02532 -0.0731 0.5753 1.0000
3.750 0.8192 0.03751 0.02623 -0.0694 0.5678 1.0000
4.000 0.8187 0.03843 0.02720 -0.0653 0.5598 1.0000
4.250 0.8423 0.03837 0.02711 -0.0645 0.5547 1.0000
4.500 0.8307 0.03976 0.02857 -0.0590 0.5462 1.0000
4.750 0.8315 0.04060 0.02944 -0.0551 0.5387 1.0000
5.000 0.8597 0.04036 0.02918 -0.0548 0.5342 1.0000
5.250 0.8201 0.04282 0.03173 -0.0457 0.5239 1.0000
5.500 0.8306 0.04323 0.03215 -0.0431 0.5177 1.0000
5.750 0.8678 0.04263 0.03153 -0.0439 0.5139 1.0000
6.000 0.7779 0.04679 0.03576 -0.0287 0.5007 1.0000
6.250 0.8090 0.04632 0.03529 -0.0285 0.4966 1.0000
6.750 0.7582 0.05056 0.03955 -0.0162 0.4785 1.0000
7.000 0.7773 0.05053 0.03952 -0.0145 0.4739 1.0000
7.250 0.7270 0.05481 0.04384 -0.0078 0.4603 1.0000
7.500 0.7401 0.05506 0.04409 -0.0056 0.4547 1.0000
8.000 0.7233 0.05869 0.04773 0.0009 0.4360 1.0000
8.500 0.7178 0.06158 0.05065 0.0064 0.4174 1.0000
9.000 0.7437 0.06165 0.05074 0.0108 0.4036 1.0000
9.500 0.7425 0.06450 0.05362 0.0155 0.3859 1.0000
10.000 0.7421 0.06752 0.05668 0.0197 0.3684 1.0000
10.500 0.7409 0.07095 0.06016 0.0234 0.3510 1.0000
11.000 0.7412 0.07444 0.06370 0.0267 0.3337 1.0000
11.500 0.7401 0.07839 0.06770 0.0296 0.3165 1.0000
12.000 0.7382 0.08270 0.07207 0.0321 0.2994 1.0000
12.250 0.7128 0.08844 0.07783 0.0324 0.2866 1.0000
12.500 0.7313 0.08813 0.07754 0.0339 0.2826 1.0000
12.750 0.7572 0.08687 0.07632 0.0356 0.2804 1.0000
13.250 0.7186 0.09767 0.08717 0.0354 0.2609 1.0000
13.750 0.7149 0.10370 0.09326 0.0361 0.2483 1.0000
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Polar data table (+)
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