GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 377 AIRFOIL (goe377-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.81 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe377-il-1000000.txt Download as CSV file: xf-goe377-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 377 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3847 0.08684 0.08530 -0.0237 1.0000 0.0091
-7.750 -0.3869 0.08499 0.08348 -0.0226 1.0000 0.0093
-7.500 -0.3991 0.08347 0.08200 -0.0200 1.0000 0.0093
-7.250 -0.3942 0.08052 0.07908 -0.0220 0.9990 0.0095
-7.000 -0.3691 0.07578 0.07432 -0.0298 0.9962 0.0098
-6.750 -0.3438 0.07100 0.06951 -0.0373 0.9930 0.0103
-6.500 -0.3183 0.06620 0.06468 -0.0444 0.9889 0.0108
-6.250 -0.2822 0.06022 0.05862 -0.0543 0.9853 0.0123
-6.000 -0.2492 0.05517 0.05349 -0.0612 0.9832 0.0124
-5.750 -0.2223 0.04979 0.04802 -0.0662 0.9772 0.0125
-5.500 -0.2171 0.01527 0.01168 -0.0760 0.9641 0.0096
-5.000 -0.1571 0.01345 0.00954 -0.0773 0.9568 0.0112
-4.750 -0.1323 0.01218 0.00800 -0.0766 0.9501 0.0121
-4.500 -0.1040 0.01135 0.00696 -0.0767 0.9448 0.0126
-4.250 -0.0793 0.00976 0.00508 -0.0761 0.9384 0.0142
-4.000 -0.0513 0.00966 0.00495 -0.0760 0.9320 0.0154
-3.750 -0.0234 0.00943 0.00465 -0.0758 0.9259 0.0169
-3.500 0.0042 0.00955 0.00473 -0.0756 0.9188 0.0178
-3.250 0.0299 0.00885 0.00395 -0.0752 0.9118 0.0205
-3.000 0.0568 0.00884 0.00390 -0.0748 0.9028 0.0225
-2.750 0.0830 0.00874 0.00374 -0.0743 0.8916 0.0242
-2.500 0.1101 0.00900 0.00396 -0.0739 0.8795 0.0252
-2.250 0.1336 0.00802 0.00287 -0.0729 0.8675 0.0289
-2.000 0.1596 0.00787 0.00266 -0.0724 0.8562 0.0308
-1.750 0.1855 0.00772 0.00245 -0.0718 0.8445 0.0327
-1.500 0.2115 0.00756 0.00224 -0.0713 0.8323 0.0342
-1.250 0.2374 0.00744 0.00206 -0.0708 0.8192 0.0352
-1.000 0.2619 0.00710 0.00163 -0.0700 0.8045 0.0374
-0.750 0.2869 0.00690 0.00135 -0.0692 0.7885 0.0395
-0.500 0.3123 0.00680 0.00118 -0.0685 0.7705 0.0411
-0.250 0.3377 0.00675 0.00105 -0.0679 0.7521 0.0428
0.000 0.3629 0.00673 0.00095 -0.0672 0.7328 0.0453
0.250 0.3883 0.00674 0.00088 -0.0666 0.7121 0.0481
0.500 0.4128 0.00669 0.00080 -0.0658 0.6900 0.0686
0.750 0.4359 0.00642 0.00082 -0.0649 0.6671 0.2131
1.000 0.4419 0.00493 0.00091 -0.0607 0.6475 0.8223
1.250 0.5587 0.00501 0.00108 -0.0809 0.6002 1.0000
1.500 0.5820 0.00517 0.00110 -0.0799 0.5731 1.0000
1.750 0.6055 0.00533 0.00114 -0.0790 0.5483 1.0000
2.000 0.6293 0.00548 0.00119 -0.0781 0.5254 1.0000
2.250 0.6530 0.00564 0.00125 -0.0773 0.5032 1.0000
2.500 0.6763 0.00584 0.00133 -0.0763 0.4744 1.0000
2.750 0.6993 0.00606 0.00142 -0.0753 0.4404 1.0000
3.000 0.7222 0.00631 0.00152 -0.0743 0.4074 1.0000
3.250 0.7452 0.00655 0.00163 -0.0734 0.3777 1.0000
3.500 0.7682 0.00680 0.00177 -0.0725 0.3508 1.0000
4.000 0.8135 0.00736 0.00208 -0.0705 0.2946 1.0000
4.250 0.8369 0.00759 0.00223 -0.0696 0.2746 1.0000
4.500 0.8604 0.00781 0.00239 -0.0688 0.2579 1.0000
4.750 0.8835 0.00806 0.00258 -0.0679 0.2376 1.0000
5.000 0.9062 0.00835 0.00276 -0.0670 0.2153 1.0000
5.250 0.9289 0.00864 0.00297 -0.0660 0.1925 1.0000
5.500 0.9481 0.00924 0.00329 -0.0646 0.1392 1.0000
5.750 0.9636 0.01020 0.00386 -0.0625 0.0672 1.0000
6.000 0.9803 0.01110 0.00449 -0.0605 0.0201 1.0000
6.250 1.0023 0.01148 0.00490 -0.0594 0.0151 1.0000
6.500 1.0238 0.01194 0.00539 -0.0581 0.0128 1.0000
6.750 1.0431 0.01262 0.00621 -0.0565 0.0110 1.0000
7.000 1.0650 0.01300 0.00662 -0.0554 0.0106 1.0000
7.250 1.0867 0.01339 0.00707 -0.0543 0.0098 1.0000
7.500 1.1070 0.01392 0.00766 -0.0530 0.0090 1.0000
7.750 1.1265 0.01450 0.00830 -0.0515 0.0085 1.0000
8.000 1.1446 0.01519 0.00906 -0.0499 0.0079 1.0000
8.250 1.1595 0.01616 0.01012 -0.0477 0.0075 1.0000
8.500 1.1630 0.01816 0.01230 -0.0436 0.0070 1.0000
8.750 1.1828 0.01862 0.01283 -0.0423 0.0069 1.0000
9.000 1.1987 0.01945 0.01374 -0.0403 0.0067 1.0000
9.250 1.2158 0.02013 0.01451 -0.0386 0.0062 1.0000
9.500 1.2290 0.02120 0.01567 -0.0363 0.0061 1.0000
9.750 1.2439 0.02202 0.01656 -0.0344 0.0057 1.0000
10.000 1.2566 0.02301 0.01763 -0.0322 0.0054 1.0000
10.250 1.2673 0.02399 0.01870 -0.0297 0.0053 1.0000
10.500 1.2743 0.02526 0.02009 -0.0266 0.0052 1.0000
10.750 1.2809 0.02658 0.02152 -0.0236 0.0051 1.0000
11.000 1.2883 0.02772 0.02277 -0.0209 0.0050 1.0000
11.250 1.2925 0.02934 0.02450 -0.0181 0.0049 1.0000
11.500 1.2960 0.03098 0.02626 -0.0154 0.0048 1.0000
11.750 1.2972 0.03291 0.02832 -0.0128 0.0047 1.0000
12.000 1.2959 0.03519 0.03076 -0.0103 0.0046 1.0000
12.250 1.2899 0.03810 0.03385 -0.0077 0.0045 1.0000
12.500 1.2815 0.04128 0.03723 -0.0055 0.0045 1.0000
12.750 1.2699 0.04487 0.04103 -0.0038 0.0045 1.0000
13.000 1.2463 0.05024 0.04667 -0.0025 0.0044 1.0000
13.250 1.2420 0.05315 0.04971 -0.0025 0.0044 1.0000
13.500 1.2154 0.05931 0.05615 -0.0039 0.0043 1.0000
13.750 1.1994 0.06472 0.06173 -0.0057 0.0043 1.0000
14.250 1.1760 0.07539 0.07269 -0.0110 0.0042 1.0000
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