GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 623 AIRFOIL (goe623-il) Reynolds number: 500,000 Max Cl/Cd: 91.27 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe623-il-500000-n5.txt Download as CSV file: xf-goe623-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 623 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7254 0.07605 0.07353 -0.0474 1.0000 0.0133
-13.000 -0.9052 0.03709 0.03393 -0.0804 1.0000 0.0121
-12.750 -0.9112 0.03398 0.03060 -0.0799 1.0000 0.0123
-12.500 -0.9115 0.03162 0.02802 -0.0784 1.0000 0.0126
-12.250 -0.9089 0.02965 0.02585 -0.0765 1.0000 0.0128
-12.000 -0.9032 0.02793 0.02391 -0.0745 0.9998 0.0131
-11.750 -0.8761 0.02671 0.02262 -0.0760 0.9964 0.0135
-11.500 -0.8468 0.02587 0.02170 -0.0774 0.9933 0.0139
-11.250 -0.8170 0.02508 0.02082 -0.0788 0.9887 0.0144
-11.000 -0.7861 0.02421 0.01983 -0.0804 0.9836 0.0150
-10.750 -0.7575 0.02317 0.01863 -0.0816 0.9758 0.0157
-10.500 -0.7301 0.02201 0.01723 -0.0825 0.9669 0.0164
-10.250 -0.7016 0.02116 0.01627 -0.0834 0.9576 0.0169
-10.000 -0.6721 0.02067 0.01571 -0.0842 0.9481 0.0174
-9.750 -0.6450 0.02018 0.01515 -0.0844 0.9378 0.0179
-9.500 -0.6186 0.01965 0.01450 -0.0845 0.9285 0.0185
-9.250 -0.5931 0.01909 0.01381 -0.0843 0.9188 0.0193
-9.000 -0.5680 0.01852 0.01306 -0.0840 0.9097 0.0201
-8.500 -0.5186 0.01726 0.01154 -0.0833 0.8927 0.0214
-8.000 -0.4673 0.01643 0.01056 -0.0828 0.8773 0.0226
-7.750 -0.4414 0.01605 0.01007 -0.0825 0.8698 0.0234
-7.500 -0.4152 0.01561 0.00952 -0.0823 0.8627 0.0242
-7.250 -0.3890 0.01518 0.00897 -0.0820 0.8558 0.0250
-7.000 -0.3623 0.01484 0.00853 -0.0818 0.8490 0.0256
-6.750 -0.3361 0.01435 0.00792 -0.0815 0.8415 0.0262
-6.500 -0.3107 0.01368 0.00718 -0.0812 0.8346 0.0271
-6.250 -0.2842 0.01324 0.00670 -0.0810 0.8272 0.0278
-6.000 -0.2574 0.01290 0.00628 -0.0809 0.8205 0.0286
-5.750 -0.2303 0.01255 0.00588 -0.0807 0.8130 0.0294
-5.500 -0.2034 0.01223 0.00547 -0.0805 0.8055 0.0301
-5.250 -0.1761 0.01190 0.00509 -0.0804 0.7970 0.0307
-5.000 -0.1488 0.01164 0.00474 -0.0802 0.7886 0.0314
-4.750 -0.1212 0.01141 0.00444 -0.0801 0.7795 0.0321
-4.500 -0.0939 0.01112 0.00409 -0.0799 0.7708 0.0327
-4.250 -0.0666 0.01082 0.00372 -0.0798 0.7606 0.0337
-4.000 -0.0391 0.01058 0.00343 -0.0797 0.7496 0.0347
-3.750 -0.0115 0.01040 0.00318 -0.0795 0.7375 0.0358
-3.500 0.0161 0.01024 0.00296 -0.0794 0.7245 0.0371
-3.250 0.0437 0.01012 0.00275 -0.0793 0.7110 0.0387
-3.000 0.0714 0.01000 0.00257 -0.0792 0.6972 0.0411
-2.750 0.0989 0.00987 0.00241 -0.0790 0.6833 0.0469
-2.500 0.1262 0.00969 0.00226 -0.0789 0.6697 0.0684
-2.250 0.1535 0.00954 0.00214 -0.0788 0.6574 0.0909
-2.000 0.1810 0.00943 0.00209 -0.0788 0.6468 0.1223
-1.750 0.2089 0.00941 0.00204 -0.0787 0.6364 0.1372
-1.500 0.2368 0.00938 0.00200 -0.0787 0.6270 0.1501
-1.000 0.2927 0.00934 0.00192 -0.0787 0.6090 0.1687
-0.750 0.3203 0.00933 0.00189 -0.0787 0.5981 0.1801
-0.250 0.3754 0.00921 0.00186 -0.0786 0.5770 0.2348
0.000 0.4026 0.00908 0.00187 -0.0786 0.5672 0.2975
0.250 0.4293 0.00890 0.00189 -0.0785 0.5553 0.3781
0.500 0.4556 0.00858 0.00192 -0.0784 0.5442 0.5033
0.750 0.4809 0.00823 0.00198 -0.0780 0.5355 0.6437
1.000 0.5049 0.00793 0.00205 -0.0771 0.5276 0.7697
1.250 0.5278 0.00777 0.00214 -0.0757 0.5206 0.8625
1.500 0.5565 0.00773 0.00222 -0.0755 0.5134 0.9398
1.750 0.5941 0.00782 0.00226 -0.0775 0.5056 0.9759
2.000 0.6300 0.00791 0.00231 -0.0793 0.4959 0.9935
2.250 0.6616 0.00802 0.00236 -0.0802 0.4860 1.0000
2.500 0.6875 0.00814 0.00243 -0.0798 0.4761 1.0000
2.750 0.7139 0.00825 0.00250 -0.0796 0.4657 1.0000
3.000 0.7401 0.00838 0.00258 -0.0792 0.4544 1.0000
3.250 0.7661 0.00853 0.00267 -0.0789 0.4410 1.0000
3.500 0.7919 0.00871 0.00278 -0.0786 0.4238 1.0000
3.750 0.8169 0.00895 0.00291 -0.0781 0.4011 1.0000
4.000 0.8414 0.00925 0.00308 -0.0776 0.3742 1.0000
4.250 0.8656 0.00958 0.00327 -0.0770 0.3491 1.0000
4.500 0.8900 0.00991 0.00349 -0.0765 0.3276 1.0000
4.750 0.9145 0.01023 0.00373 -0.0760 0.3092 1.0000
5.250 0.9638 0.01084 0.00420 -0.0751 0.2784 1.0000
5.500 0.9886 0.01113 0.00444 -0.0747 0.2653 1.0000
5.750 1.0133 0.01142 0.00469 -0.0743 0.2536 1.0000
6.000 1.0377 0.01173 0.00496 -0.0738 0.2426 1.0000
6.500 1.0865 0.01233 0.00552 -0.0729 0.2240 1.0000
6.750 1.1103 0.01266 0.00582 -0.0724 0.2164 1.0000
7.000 1.1345 0.01295 0.00612 -0.0719 0.2087 1.0000
7.250 1.1577 0.01331 0.00644 -0.0713 0.2011 1.0000
7.500 1.1813 0.01362 0.00676 -0.0707 0.1933 1.0000
7.750 1.2039 0.01400 0.00711 -0.0700 0.1852 1.0000
8.000 1.2266 0.01435 0.00746 -0.0693 0.1774 1.0000
8.250 1.2488 0.01472 0.00783 -0.0686 0.1712 1.0000
8.500 1.2712 0.01507 0.00819 -0.0679 0.1645 1.0000
8.750 1.2922 0.01549 0.00860 -0.0670 0.1570 1.0000
9.000 1.3134 0.01588 0.00901 -0.0661 0.1489 1.0000
9.250 1.3333 0.01633 0.00945 -0.0650 0.1394 1.0000
9.500 1.3516 0.01685 0.00993 -0.0638 0.1271 1.0000
9.750 1.3660 0.01749 0.01049 -0.0618 0.1095 1.0000
10.000 1.3656 0.01900 0.01168 -0.0579 0.0654 1.0000
10.250 1.3725 0.02016 0.01278 -0.0552 0.0501 1.0000
10.500 1.3828 0.02115 0.01376 -0.0531 0.0408 1.0000
10.750 1.3930 0.02218 0.01478 -0.0512 0.0323 1.0000
11.000 1.4025 0.02330 0.01589 -0.0493 0.0249 1.0000
11.250 1.4119 0.02447 0.01707 -0.0475 0.0202 1.0000
11.500 1.4212 0.02569 0.01832 -0.0459 0.0175 1.0000
11.750 1.4313 0.02688 0.01958 -0.0445 0.0159 1.0000
12.000 1.4400 0.02824 0.02100 -0.0431 0.0146 1.0000
12.250 1.4473 0.02974 0.02257 -0.0417 0.0136 1.0000
12.500 1.4562 0.03117 0.02408 -0.0405 0.0130 1.0000
12.750 1.4637 0.03276 0.02576 -0.0394 0.0124 1.0000
13.000 1.4696 0.03453 0.02761 -0.0384 0.0118 1.0000
13.250 1.4740 0.03651 0.02968 -0.0374 0.0113 1.0000
13.500 1.4762 0.03877 0.03203 -0.0365 0.0109 1.0000
13.750 1.4770 0.04125 0.03461 -0.0357 0.0105 1.0000
14.000 1.4799 0.04360 0.03706 -0.0352 0.0102 1.0000
14.250 1.4817 0.04614 0.03971 -0.0349 0.0099 1.0000
14.500 1.4819 0.04892 0.04260 -0.0346 0.0096 1.0000
14.750 1.4810 0.05194 0.04572 -0.0345 0.0093 1.0000
15.000 1.4794 0.05515 0.04904 -0.0346 0.0090 1.0000
15.250 1.4759 0.05866 0.05266 -0.0349 0.0088 1.0000
15.500 1.4708 0.06249 0.05659 -0.0353 0.0086 1.0000
15.750 1.4640 0.06663 0.06084 -0.0360 0.0084 1.0000
16.000 1.4553 0.07114 0.06547 -0.0368 0.0083 1.0000
16.250 1.4447 0.07600 0.07044 -0.0378 0.0082 1.0000
16.500 1.4318 0.08133 0.07590 -0.0391 0.0081 1.0000
16.750 1.4201 0.08664 0.08134 -0.0406 0.0080 1.0000
17.000 1.4096 0.09183 0.08665 -0.0420 0.0079 1.0000
17.250 1.3983 0.09727 0.09222 -0.0437 0.0078 1.0000
17.500 1.3866 0.10290 0.09797 -0.0456 0.0077 1.0000
17.750 1.3750 0.10859 0.10378 -0.0476 0.0077 1.0000
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