GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 599 AIRFOIL (goe599-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.78 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe599-il-1000000.txt Download as CSV file: xf-goe599-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 599 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8638 0.07023 0.06833 -0.0356 1.0000 0.0078
-13.000 -0.9163 0.05300 0.05082 -0.0499 1.0000 0.0076
-12.750 -0.9429 0.04371 0.04127 -0.0587 1.0000 0.0075
-12.500 -0.9614 0.03848 0.03582 -0.0619 1.0000 0.0075
-12.250 -0.9772 0.03544 0.03259 -0.0603 1.0000 0.0076
-12.000 -0.9859 0.03314 0.03011 -0.0574 1.0000 0.0076
-11.750 -0.9892 0.03099 0.02777 -0.0546 1.0000 0.0077
-11.500 -0.9880 0.02913 0.02572 -0.0518 1.0000 0.0079
-11.250 -0.9840 0.02741 0.02381 -0.0491 1.0000 0.0080
-11.000 -0.9768 0.02588 0.02209 -0.0466 1.0000 0.0081
-10.750 -0.9667 0.02453 0.02058 -0.0444 1.0000 0.0083
-10.500 -0.9540 0.02339 0.01928 -0.0424 1.0000 0.0084
-10.250 -0.9388 0.02247 0.01822 -0.0406 1.0000 0.0086
-10.000 -0.9291 0.02050 0.01600 -0.0383 1.0000 0.0088
-9.750 -0.9169 0.01877 0.01408 -0.0363 1.0000 0.0092
-9.500 -0.8983 0.01805 0.01330 -0.0350 1.0000 0.0096
-9.250 -0.8780 0.01756 0.01275 -0.0339 1.0000 0.0099
-9.000 -0.8574 0.01709 0.01223 -0.0329 1.0000 0.0103
-8.750 -0.8357 0.01655 0.01162 -0.0320 0.9999 0.0108
-8.500 -0.8050 0.01589 0.01087 -0.0331 0.9990 0.0112
-8.250 -0.7737 0.01531 0.01020 -0.0342 0.9979 0.0116
-8.000 -0.7447 0.01402 0.00876 -0.0351 0.9967 0.0123
-7.750 -0.7127 0.01341 0.00810 -0.0364 0.9956 0.0131
-7.500 -0.6795 0.01302 0.00768 -0.0379 0.9947 0.0139
-7.250 -0.6471 0.01262 0.00723 -0.0392 0.9936 0.0148
-7.000 -0.6157 0.01233 0.00690 -0.0401 0.9918 0.0155
-6.750 -0.5849 0.01155 0.00607 -0.0411 0.9900 0.0171
-6.500 -0.5517 0.01125 0.00577 -0.0425 0.9884 0.0184
-6.250 -0.5177 0.01097 0.00546 -0.0440 0.9870 0.0198
-6.000 -0.4837 0.01050 0.00493 -0.0456 0.9858 0.0216
-5.750 -0.4489 0.01014 0.00459 -0.0473 0.9848 0.0242
-5.500 -0.4132 0.00993 0.00436 -0.0492 0.9839 0.0264
-5.250 -0.3807 0.00950 0.00390 -0.0503 0.9821 0.0293
-5.000 -0.3499 0.00918 0.00357 -0.0511 0.9790 0.0326
-4.750 -0.3158 0.00896 0.00333 -0.0526 0.9770 0.0351
-4.500 -0.2818 0.00861 0.00297 -0.0540 0.9750 0.0404
-4.250 -0.2480 0.00833 0.00269 -0.0554 0.9730 0.0462
-4.000 -0.2155 0.00785 0.00245 -0.0566 0.9708 0.0947
-3.750 -0.1888 0.00764 0.00228 -0.0563 0.9648 0.1099
-3.500 -0.1594 0.00740 0.00208 -0.0566 0.9598 0.1228
-3.250 -0.1318 0.00704 0.00187 -0.0567 0.9536 0.1615
-3.000 -0.1060 0.00664 0.00168 -0.0563 0.9435 0.2257
-2.750 -0.0800 0.00637 0.00152 -0.0558 0.9291 0.2644
-2.500 -0.0536 0.00615 0.00138 -0.0554 0.9123 0.3008
-2.250 -0.0266 0.00594 0.00126 -0.0552 0.8960 0.3403
-2.000 0.0001 0.00570 0.00116 -0.0550 0.8794 0.3981
-1.750 0.0269 0.00550 0.00109 -0.0548 0.8634 0.4559
-1.500 0.0540 0.00538 0.00105 -0.0547 0.8492 0.5022
-1.250 0.0810 0.00529 0.00103 -0.0545 0.8340 0.5489
-1.000 0.1080 0.00526 0.00101 -0.0543 0.8173 0.5820
-0.750 0.1355 0.00523 0.00100 -0.0542 0.8034 0.6080
-0.500 0.1628 0.00519 0.00100 -0.0540 0.7895 0.6393
-0.250 0.1900 0.00514 0.00101 -0.0538 0.7739 0.6707
0.000 0.2173 0.00509 0.00101 -0.0537 0.7600 0.7020
0.250 0.2445 0.00503 0.00103 -0.0535 0.7463 0.7360
0.500 0.2713 0.00499 0.00105 -0.0532 0.7286 0.7734
0.750 0.2973 0.00495 0.00108 -0.0527 0.7071 0.8125
1.000 0.3224 0.00497 0.00112 -0.0520 0.6755 0.8528
1.250 0.3459 0.00507 0.00117 -0.0509 0.6316 0.8924
1.500 0.3684 0.00528 0.00126 -0.0495 0.5788 0.9289
1.750 0.3930 0.00563 0.00138 -0.0488 0.5068 0.9604
2.000 0.4229 0.00611 0.00153 -0.0494 0.4246 0.9793
2.250 0.4558 0.00660 0.00170 -0.0509 0.3490 0.9906
2.500 0.4895 0.00775 0.00207 -0.0530 0.1658 0.9987
2.750 0.5130 0.00847 0.00236 -0.0524 0.0702 1.0000
3.000 0.5369 0.00869 0.00253 -0.0517 0.0612 1.0000
3.250 0.5617 0.00887 0.00270 -0.0510 0.0586 1.0000
3.500 0.5869 0.00904 0.00288 -0.0505 0.0572 1.0000
3.750 0.6124 0.00922 0.00307 -0.0501 0.0555 1.0000
4.000 0.6379 0.00944 0.00330 -0.0496 0.0538 1.0000
4.250 0.6634 0.00968 0.00354 -0.0492 0.0521 1.0000
4.500 0.6887 0.00997 0.00384 -0.0487 0.0502 1.0000
4.750 0.7131 0.01038 0.00429 -0.0481 0.0480 1.0000
5.000 0.7378 0.01074 0.00469 -0.0476 0.0465 1.0000
5.250 0.7648 0.01083 0.00477 -0.0475 0.0454 1.0000
5.500 0.7908 0.01104 0.00500 -0.0472 0.0442 1.0000
5.750 0.8166 0.01127 0.00525 -0.0469 0.0428 1.0000
6.000 0.8426 0.01148 0.00546 -0.0467 0.0410 1.0000
6.250 0.8682 0.01173 0.00571 -0.0464 0.0392 1.0000
6.500 0.8899 0.01243 0.00645 -0.0454 0.0364 1.0000
6.750 0.9175 0.01244 0.00647 -0.0454 0.0356 1.0000
7.000 0.9452 0.01244 0.00647 -0.0455 0.0339 1.0000
7.250 0.9724 0.01248 0.00647 -0.0455 0.0313 1.0000
7.500 0.9980 0.01271 0.00666 -0.0452 0.0277 1.0000
7.750 1.0244 0.01284 0.00675 -0.0451 0.0236 1.0000
8.000 1.0486 0.01322 0.00709 -0.0446 0.0193 1.0000
8.250 1.0714 0.01373 0.00759 -0.0438 0.0163 1.0000
8.500 1.0948 0.01417 0.00806 -0.0431 0.0148 1.0000
8.750 1.1168 0.01474 0.00865 -0.0423 0.0133 1.0000
9.000 1.1376 0.01544 0.00943 -0.0412 0.0123 1.0000
9.250 1.1599 0.01594 0.01000 -0.0403 0.0118 1.0000
9.500 1.1815 0.01651 0.01062 -0.0394 0.0111 1.0000
9.750 1.2024 0.01712 0.01128 -0.0384 0.0106 1.0000
10.000 1.2215 0.01790 0.01212 -0.0371 0.0100 1.0000
10.250 1.2338 0.01935 0.01371 -0.0348 0.0093 1.0000
10.500 1.2543 0.01991 0.01436 -0.0338 0.0091 1.0000
10.750 1.2737 0.02055 0.01507 -0.0326 0.0088 1.0000
11.000 1.2919 0.02126 0.01587 -0.0313 0.0085 1.0000
11.250 1.3092 0.02202 0.01670 -0.0299 0.0082 1.0000
11.500 1.3249 0.02284 0.01761 -0.0283 0.0079 1.0000
11.750 1.3381 0.02370 0.01855 -0.0262 0.0076 1.0000
12.000 1.3490 0.02463 0.01956 -0.0239 0.0074 1.0000
12.250 1.3567 0.02581 0.02083 -0.0212 0.0072 1.0000
12.500 1.3582 0.02752 0.02270 -0.0179 0.0070 1.0000
12.750 1.3505 0.03011 0.02552 -0.0140 0.0068 1.0000
13.000 1.3537 0.03178 0.02734 -0.0116 0.0067 1.0000
13.250 1.3600 0.03322 0.02889 -0.0098 0.0066 1.0000
13.500 1.3637 0.03495 0.03076 -0.0080 0.0065 1.0000
13.750 1.3652 0.03696 0.03291 -0.0064 0.0064 1.0000
14.000 1.3652 0.03924 0.03534 -0.0051 0.0063 1.0000
14.250 1.3622 0.04197 0.03823 -0.0041 0.0063 1.0000
14.500 1.3579 0.04500 0.04141 -0.0035 0.0062 1.0000
14.750 1.3503 0.04864 0.04520 -0.0034 0.0062 1.0000
15.000 1.3411 0.05271 0.04944 -0.0039 0.0061 1.0000
15.250 1.3303 0.05734 0.05423 -0.0051 0.0060 1.0000
15.500 1.3149 0.06297 0.06003 -0.0071 0.0060 1.0000
15.750 1.2987 0.06923 0.06646 -0.0100 0.0060 1.0000
16.000 1.2758 0.07718 0.07459 -0.0142 0.0060 1.0000
16.250 1.2502 0.08623 0.08381 -0.0192 0.0061 1.0000
16.500 1.2192 0.09687 0.09464 -0.0253 0.0061 1.0000
16.750 1.1804 0.10964 0.10758 -0.0324 0.0062 1.0000
17.000 1.1274 0.12674 0.12489 -0.0416 0.0064 1.0000
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