GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 376 AIRFOIL (goe376-il) Reynolds number: 100,000 Max Cl/Cd: 58.66 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe376-il-100000-n5.txt Download as CSV file: xf-goe376-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 376 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3032 0.10019 0.09538 -0.0239 1.0000 0.0302
-7.750 -0.3071 0.09878 0.09407 -0.0242 1.0000 0.0305
-7.500 -0.3105 0.09719 0.09258 -0.0247 1.0000 0.0306
-7.250 -0.3094 0.09527 0.09074 -0.0267 1.0000 0.0308
-7.000 -0.3062 0.09319 0.08872 -0.0291 1.0000 0.0309
-6.750 -0.3010 0.09101 0.08657 -0.0314 1.0000 0.0310
-6.500 -0.3024 0.08553 0.08119 -0.0244 1.0000 0.0320
-6.250 -0.3013 0.08293 0.07865 -0.0229 1.0000 0.0329
-6.000 -0.3006 0.08067 0.07646 -0.0222 1.0000 0.0338
-5.750 -0.2998 0.07847 0.07430 -0.0219 1.0000 0.0348
-5.500 -0.2742 0.07462 0.07041 -0.0278 0.9949 0.0367
-5.250 -0.1610 0.05175 0.04768 -0.0461 0.9596 0.0421
-5.000 -0.1342 0.04734 0.04321 -0.0504 0.9508 0.0462
-4.750 -0.0804 0.04431 0.03971 -0.0641 0.9396 0.0512
-4.500 -0.0689 0.03848 0.03402 -0.0637 0.9310 0.0528
-4.250 -0.0431 0.03454 0.03005 -0.0661 0.9242 0.0566
-4.000 -0.0042 0.03134 0.02650 -0.0726 0.9144 0.0652
-3.750 0.0196 0.02757 0.02275 -0.0740 0.9079 0.0697
-3.500 0.0580 0.02520 0.01995 -0.0786 0.8969 0.0790
-3.250 0.0793 0.02190 0.01670 -0.0793 0.8877 0.0829
-3.000 0.1141 0.01946 0.01395 -0.0823 0.8786 0.0946
-2.750 0.1415 0.01755 0.01181 -0.0836 0.8665 0.1085
-2.500 0.1671 0.01570 0.00985 -0.0842 0.8547 0.1193
-2.250 0.1927 0.01366 0.00769 -0.0849 0.8434 0.1282
-2.000 0.2199 0.01210 0.00594 -0.0856 0.8316 0.1437
-1.500 0.2870 0.02540 0.01787 -0.0884 0.8375 0.0732
-1.250 0.3199 0.02396 0.01592 -0.0881 0.8246 0.0625
-1.000 0.3487 0.02241 0.01417 -0.0881 0.8110 0.0591
-0.750 0.3786 0.02118 0.01262 -0.0879 0.7972 0.0557
-0.500 0.4091 0.02026 0.01128 -0.0874 0.7832 0.0526
-0.250 0.4384 0.01980 0.01056 -0.0871 0.7685 0.0513
0.000 0.4667 0.01892 0.00950 -0.0868 0.7535 0.0508
0.250 0.4947 0.01832 0.00872 -0.0864 0.7380 0.0511
0.500 0.5217 0.01753 0.00785 -0.0860 0.7221 0.0533
0.750 0.5484 0.01706 0.00729 -0.0854 0.7053 0.0542
1.000 0.5748 0.01665 0.00678 -0.0847 0.6870 0.0539
1.250 0.6004 0.01632 0.00634 -0.0839 0.6670 0.0538
1.500 0.6251 0.01606 0.00600 -0.0829 0.6456 0.0540
1.750 0.6510 0.01591 0.00570 -0.0822 0.6250 0.0544
2.000 0.6768 0.01584 0.00550 -0.0815 0.6054 0.0552
2.250 0.7025 0.01583 0.00536 -0.0809 0.5866 0.0562
2.500 0.7281 0.01587 0.00526 -0.0802 0.5682 0.0578
2.750 0.7535 0.01596 0.00524 -0.0795 0.5509 0.0613
3.000 0.7789 0.01606 0.00527 -0.0789 0.5343 0.0696
3.250 0.8041 0.01618 0.00535 -0.0783 0.5181 0.0879
3.500 0.8507 0.01490 0.00561 -0.0827 0.4993 1.0000
3.750 0.8746 0.01520 0.00577 -0.0818 0.4845 1.0000
4.000 0.8983 0.01551 0.00596 -0.0809 0.4701 1.0000
4.250 0.9219 0.01585 0.00619 -0.0800 0.4561 1.0000
4.500 0.9452 0.01619 0.00647 -0.0791 0.4419 1.0000
4.750 0.9683 0.01656 0.00676 -0.0782 0.4275 1.0000
5.000 0.9912 0.01692 0.00709 -0.0772 0.4131 1.0000
5.250 1.0139 0.01729 0.00746 -0.0763 0.3982 1.0000
5.500 1.0365 0.01767 0.00783 -0.0753 0.3835 1.0000
5.750 1.0588 0.01805 0.00822 -0.0743 0.3686 1.0000
6.000 1.0810 0.01844 0.00864 -0.0733 0.3541 1.0000
6.250 1.1030 0.01885 0.00911 -0.0723 0.3398 1.0000
6.500 1.1249 0.01927 0.00959 -0.0713 0.3263 1.0000
6.750 1.1465 0.01973 0.01010 -0.0702 0.3134 1.0000
7.000 1.1678 0.02021 0.01064 -0.0691 0.3009 1.0000
7.250 1.1880 0.02072 0.01120 -0.0679 0.2866 1.0000
7.500 1.2061 0.02126 0.01170 -0.0664 0.2669 1.0000
7.750 1.2232 0.02186 0.01226 -0.0648 0.2445 1.0000
8.000 1.2411 0.02250 0.01291 -0.0634 0.2275 1.0000
8.250 1.2587 0.02315 0.01365 -0.0619 0.2116 1.0000
8.500 1.2765 0.02381 0.01439 -0.0605 0.1978 1.0000
8.750 1.2932 0.02452 0.01517 -0.0589 0.1804 1.0000
9.000 1.3073 0.02539 0.01600 -0.0571 0.1517 1.0000
9.250 1.3197 0.02643 0.01698 -0.0550 0.1228 1.0000
9.500 1.3168 0.02875 0.01867 -0.0515 0.0539 1.0000
9.750 1.3159 0.03079 0.02054 -0.0480 0.0312 1.0000
10.000 1.3175 0.03247 0.02229 -0.0447 0.0261 1.0000
10.250 1.3194 0.03414 0.02406 -0.0418 0.0238 1.0000
10.500 1.3189 0.03604 0.02611 -0.0389 0.0223 1.0000
10.750 1.3187 0.03797 0.02823 -0.0364 0.0215 1.0000
11.000 1.3173 0.04008 0.03056 -0.0343 0.0209 1.0000
11.250 1.3140 0.04251 0.03321 -0.0325 0.0205 1.0000
11.500 1.3090 0.04528 0.03620 -0.0312 0.0201 1.0000
11.750 1.3021 0.04847 0.03960 -0.0304 0.0197 1.0000
12.000 1.2945 0.05201 0.04334 -0.0302 0.0194 1.0000
12.250 1.2850 0.05605 0.04758 -0.0305 0.0189 1.0000
12.500 1.2746 0.06049 0.05220 -0.0312 0.0185 1.0000
12.750 1.2645 0.06515 0.05704 -0.0324 0.0184 1.0000
13.000 1.2532 0.07021 0.06230 -0.0339 0.0180 1.0000
13.250 1.2430 0.07529 0.06754 -0.0356 0.0179 1.0000
13.500 1.2308 0.08085 0.07324 -0.0376 0.0173 1.0000
13.750 1.2221 0.08589 0.07843 -0.0392 0.0172 1.0000
14.000 1.2125 0.09114 0.08380 -0.0411 0.0168 1.0000
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Polar data table (+)
Polar graphs
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