GOE 627 AIRFOIL (goe627-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 627 AIRFOIL (goe627-il) Reynolds number: 100,000 Max Cl/Cd: 41.45 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe627-il-100000-n5.txt Download as CSV file: xf-goe627-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 627 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4221 0.09392 0.08897 -0.0477 1.0000 0.0429
-10.500 -0.4375 0.08897 0.08407 -0.0486 1.0000 0.0427
-10.250 -0.4593 0.08271 0.07786 -0.0506 1.0000 0.0423
-10.000 -0.4958 0.07558 0.07072 -0.0537 1.0000 0.0419
-9.750 -0.5297 0.06874 0.06372 -0.0579 0.9953 0.0416
-9.500 -0.5542 0.06344 0.05817 -0.0593 0.9863 0.0413
-9.250 -0.5687 0.05801 0.05236 -0.0599 0.9773 0.0413
-9.000 -0.5773 0.05276 0.04657 -0.0597 0.9690 0.0420
-8.750 -0.5818 0.04844 0.04162 -0.0581 0.9602 0.0427
-8.500 -0.5695 0.04584 0.03876 -0.0575 0.9543 0.0434
-8.250 -0.5530 0.04397 0.03675 -0.0568 0.9477 0.0440
-8.000 -0.5311 0.04170 0.03420 -0.0572 0.9432 0.0446
-7.750 -0.5194 0.03982 0.03204 -0.0552 0.9354 0.0452
-7.500 -0.4977 0.03795 0.02988 -0.0549 0.9298 0.0463
-7.250 -0.4714 0.03609 0.02761 -0.0552 0.9258 0.0477
-7.000 -0.4589 0.03464 0.02581 -0.0526 0.9167 0.0486
-6.750 -0.4300 0.03304 0.02391 -0.0530 0.9123 0.0494
-6.500 -0.4056 0.03182 0.02264 -0.0526 0.9062 0.0502
-6.250 -0.3811 0.03078 0.02151 -0.0521 0.8992 0.0512
-6.000 -0.3476 0.02973 0.02035 -0.0532 0.8953 0.0530
-5.750 -0.3269 0.02889 0.01937 -0.0518 0.8867 0.0545
-5.500 -0.2952 0.02787 0.01819 -0.0522 0.8813 0.0558
-5.250 -0.2579 0.02674 0.01705 -0.0538 0.8779 0.0571
-5.000 -0.2402 0.02606 0.01639 -0.0518 0.8671 0.0581
-4.750 -0.2043 0.02514 0.01545 -0.0531 0.8627 0.0606
-4.500 -0.1844 0.02456 0.01482 -0.0513 0.8521 0.0628
-4.250 -0.1507 0.02365 0.01390 -0.0521 0.8470 0.0653
-4.000 -0.1309 0.02304 0.01329 -0.0503 0.8365 0.0675
-3.750 -0.0982 0.02224 0.01245 -0.0508 0.8306 0.0708
-3.500 -0.0772 0.02170 0.01187 -0.0491 0.8199 0.0745
-3.250 -0.0436 0.02090 0.01104 -0.0498 0.8134 0.0828
-3.000 -0.0231 0.02031 0.01053 -0.0481 0.8017 0.0933
-2.750 0.0116 0.01928 0.00982 -0.0490 0.7951 0.1443
-2.500 0.0290 0.01851 0.00953 -0.0470 0.7823 0.2445
-2.250 0.0550 0.01775 0.00916 -0.0464 0.7716 0.3514
-2.000 0.0834 0.01681 0.00882 -0.0461 0.7615 0.4897
-1.750 0.1130 0.01609 0.00894 -0.0453 0.7486 0.6945
-1.500 0.1960 0.01623 0.00938 -0.0538 0.7360 0.8552
-1.250 0.2498 0.01634 0.00929 -0.0577 0.7197 0.8890
-1.000 0.3041 0.01646 0.00919 -0.0621 0.7010 0.9091
-0.750 0.3523 0.01659 0.00908 -0.0655 0.6809 0.9244
-0.500 0.4019 0.01670 0.00894 -0.0694 0.6594 0.9338
-0.250 0.4432 0.01680 0.00880 -0.0718 0.6384 0.9436
0.000 0.4825 0.01694 0.00873 -0.0739 0.6163 0.9538
0.250 0.5297 0.01712 0.00870 -0.0776 0.5922 0.9652
0.500 0.5792 0.01731 0.00864 -0.0819 0.5671 0.9778
0.750 0.6237 0.01743 0.00856 -0.0854 0.5429 0.9877
1.000 0.6622 0.01755 0.00848 -0.0878 0.5199 0.9953
1.250 0.6929 0.01769 0.00843 -0.0888 0.4987 1.0000
1.500 0.7055 0.01787 0.00846 -0.0861 0.4815 1.0000
1.750 0.7180 0.01806 0.00851 -0.0834 0.4655 1.0000
2.000 0.7306 0.01826 0.00859 -0.0807 0.4510 1.0000
2.250 0.7430 0.01849 0.00869 -0.0779 0.4374 1.0000
2.500 0.7555 0.01873 0.00879 -0.0752 0.4250 1.0000
2.750 0.7685 0.01896 0.00894 -0.0725 0.4133 1.0000
3.000 0.7815 0.01922 0.00910 -0.0699 0.4031 1.0000
3.250 0.7945 0.01948 0.00927 -0.0672 0.3930 1.0000
3.500 0.8079 0.01975 0.00946 -0.0646 0.3838 1.0000
3.750 0.8211 0.02004 0.00966 -0.0620 0.3749 1.0000
4.000 0.8351 0.02034 0.00988 -0.0595 0.3668 1.0000
4.250 0.8489 0.02064 0.01012 -0.0570 0.3589 1.0000
4.500 0.8637 0.02097 0.01035 -0.0547 0.3523 1.0000
4.750 0.8788 0.02128 0.01066 -0.0525 0.3454 1.0000
5.000 0.8943 0.02163 0.01093 -0.0503 0.3396 1.0000
5.250 0.9104 0.02199 0.01123 -0.0483 0.3341 1.0000
5.500 0.9255 0.02233 0.01158 -0.0461 0.3282 1.0000
5.750 0.9407 0.02270 0.01189 -0.0439 0.3229 1.0000
6.000 0.9576 0.02310 0.01222 -0.0421 0.3182 1.0000
6.250 0.9729 0.02347 0.01263 -0.0400 0.3130 1.0000
6.500 0.9893 0.02387 0.01302 -0.0381 0.3085 1.0000
6.750 1.0077 0.02431 0.01340 -0.0366 0.3048 1.0000
7.000 1.0265 0.02477 0.01384 -0.0353 0.3010 1.0000
7.250 1.0421 0.02522 0.01437 -0.0333 0.2968 1.0000
7.500 1.0587 0.02568 0.01485 -0.0316 0.2928 1.0000
7.750 1.0761 0.02615 0.01529 -0.0301 0.2891 1.0000
8.000 1.0977 0.02667 0.01574 -0.0293 0.2859 1.0000
8.250 1.1121 0.02720 0.01640 -0.0273 0.2825 1.0000
8.500 1.1281 0.02776 0.01704 -0.0256 0.2792 1.0000
8.750 1.1444 0.02832 0.01764 -0.0240 0.2759 1.0000
9.000 1.1620 0.02886 0.01820 -0.0227 0.2727 1.0000
9.250 1.1827 0.02942 0.01872 -0.0219 0.2698 1.0000
9.500 1.1958 0.03009 0.01950 -0.0199 0.2667 1.0000
9.750 1.2070 0.03078 0.02033 -0.0177 0.2633 1.0000
10.000 1.2186 0.03141 0.02104 -0.0156 0.2595 1.0000
10.250 1.2325 0.03197 0.02161 -0.0139 0.2558 1.0000
10.500 1.2495 0.03254 0.02211 -0.0127 0.2521 1.0000
10.750 1.2518 0.03342 0.02321 -0.0095 0.2482 1.0000
11.000 1.2581 0.03423 0.02414 -0.0071 0.2440 1.0000
11.250 1.2686 0.03495 0.02491 -0.0052 0.2404 1.0000
11.500 1.2836 0.03560 0.02555 -0.0039 0.2374 1.0000
11.750 1.2936 0.03654 0.02660 -0.0022 0.2345 1.0000
12.000 1.2959 0.03776 0.02802 0.0002 0.2314 1.0000
12.250 1.3007 0.03893 0.02933 0.0023 0.2282 1.0000
12.500 1.3083 0.03998 0.03047 0.0039 0.2251 1.0000
12.750 1.3200 0.04085 0.03138 0.0052 0.2222 1.0000
13.000 1.3331 0.04175 0.03229 0.0062 0.2195 1.0000
13.250 1.3240 0.04379 0.03461 0.0089 0.2163 1.0000
13.500 1.3196 0.04572 0.03671 0.0108 0.2128 1.0000
13.750 1.3209 0.04735 0.03845 0.0122 0.2096 1.0000
14.000 1.3293 0.04852 0.03967 0.0132 0.2067 1.0000
14.250 1.3367 0.04984 0.04103 0.0142 0.2038 1.0000
14.500 1.3155 0.05349 0.04498 0.0158 0.2006 1.0000
14.750 1.2994 0.05704 0.04873 0.0167 0.1971 1.0000
15.000 1.2935 0.05981 0.05163 0.0172 0.1939 1.0000
15.250 1.3019 0.06123 0.05307 0.0176 0.1911 1.0000
15.500 1.2916 0.06470 0.05667 0.0177 0.1882 1.0000
15.750 1.2040 0.07812 0.07051 0.0147 0.1834 1.0000
16.000 1.1513 0.08860 0.08115 0.0113 0.1783 1.0000
16.250 1.1872 0.08620 0.07875 0.0128 0.1765 1.0000
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Polar data table (+)
Polar graphs
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