GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il) Reynolds number: 50,000 Max Cl/Cd: 29.37 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe677-il-50000.txt Download as CSV file: xf-goe677-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 677 (= M 6) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5094 0.13113 0.12398 0.0032 1.0000 0.2367
-10.250 -0.4829 0.12536 0.11817 0.0044 1.0000 0.2451
-10.000 -0.5126 0.12504 0.11799 0.0013 1.0000 0.2531
-9.750 -0.4822 0.11940 0.11230 0.0031 1.0000 0.2668
-9.500 -0.4701 0.11539 0.10830 0.0034 1.0000 0.2783
-9.250 -0.4704 0.11218 0.10515 0.0030 1.0000 0.2898
-9.000 -0.4969 0.11128 0.10438 0.0012 1.0000 0.3018
-8.750 -0.4812 0.10719 0.10028 0.0022 1.0000 0.3174
-8.500 -0.4685 0.10336 0.09647 0.0030 1.0000 0.3330
-8.250 -0.4655 0.10025 0.09340 0.0035 1.0000 0.3496
-8.000 -0.4668 0.09730 0.09054 0.0041 1.0000 0.3673
-7.750 -0.4338 0.09315 0.08634 0.0063 1.0000 0.3942
-7.500 -0.4238 0.09007 0.08329 0.0079 1.0000 0.4205
-6.750 -0.3959 0.08195 0.07530 0.0140 1.0000 0.5142
-6.500 -0.3632 0.07840 0.07171 0.0153 1.0000 0.5527
-6.250 -0.3368 0.07553 0.06883 0.0173 1.0000 0.6020
-6.000 -0.3091 0.07249 0.06579 0.0184 1.0000 0.6486
-5.500 -0.5326 0.05381 0.04673 -0.0111 1.0000 0.2306
-5.250 -0.5364 0.04980 0.04213 -0.0093 1.0000 0.2012
-5.000 -0.5349 0.04679 0.03858 -0.0069 1.0000 0.1873
-4.750 -0.5275 0.04440 0.03597 -0.0048 1.0000 0.1834
-4.500 -0.5182 0.04218 0.03341 -0.0029 1.0000 0.1812
-4.250 -0.5060 0.04009 0.03092 -0.0013 1.0000 0.1797
-4.000 -0.4905 0.03810 0.02844 0.0001 1.0000 0.1776
-3.750 -0.4727 0.03636 0.02622 0.0013 1.0000 0.1761
-3.500 -0.4535 0.03480 0.02440 0.0022 1.0000 0.1771
-3.250 -0.4335 0.03356 0.02302 0.0029 1.0000 0.1818
-3.000 -0.4121 0.03248 0.02160 0.0036 1.0000 0.1867
-2.750 -0.3894 0.03147 0.02024 0.0041 1.0000 0.1904
-2.500 -0.3668 0.03040 0.01920 0.0044 1.0000 0.1966
-2.250 -0.3441 0.02973 0.01835 0.0049 1.0000 0.2067
-2.000 -0.3197 0.02907 0.01770 0.0050 1.0000 0.2184
-1.750 -0.2872 0.02854 0.01715 0.0037 0.9982 0.2362
-1.500 -0.1306 0.02518 0.01702 -0.0151 1.0000 1.0000
-1.250 -0.0843 0.02566 0.01689 -0.0198 0.9897 1.0000
-1.000 -0.0349 0.02615 0.01698 -0.0252 0.9772 1.0000
-0.750 0.0122 0.02663 0.01717 -0.0302 0.9646 1.0000
-0.500 0.0596 0.02710 0.01739 -0.0350 0.9516 1.0000
-0.250 0.1094 0.02756 0.01765 -0.0402 0.9390 1.0000
0.000 0.1547 0.02799 0.01793 -0.0445 0.9255 1.0000
0.250 0.1954 0.02844 0.01826 -0.0478 0.9113 1.0000
0.500 0.2350 0.02892 0.01865 -0.0508 0.8973 1.0000
0.750 0.2746 0.02940 0.01906 -0.0538 0.8832 1.0000
1.000 0.3115 0.02990 0.01950 -0.0560 0.8692 1.0000
1.250 0.3460 0.03042 0.01999 -0.0578 0.8554 1.0000
1.500 0.3822 0.03089 0.02042 -0.0596 0.8422 1.0000
1.750 0.4156 0.03136 0.02089 -0.0608 0.8292 1.0000
2.000 0.4326 0.03221 0.02172 -0.0595 0.8150 1.0000
2.250 0.4482 0.03312 0.02262 -0.0580 0.8012 1.0000
2.500 0.4645 0.03406 0.02356 -0.0567 0.7885 1.0000
2.750 0.4898 0.03478 0.02430 -0.0565 0.7770 1.0000
3.000 0.5143 0.03549 0.02503 -0.0561 0.7657 1.0000
3.250 0.5184 0.03687 0.02641 -0.0532 0.7529 1.0000
3.500 0.5290 0.03809 0.02765 -0.0512 0.7413 1.0000
3.750 0.5667 0.03841 0.02803 -0.0521 0.7317 1.0000
4.000 0.5647 0.04009 0.02972 -0.0488 0.7190 1.0000
4.250 0.5668 0.04167 0.03132 -0.0459 0.7071 1.0000
4.500 0.5886 0.04257 0.03228 -0.0450 0.6961 1.0000
4.750 0.6157 0.04319 0.03298 -0.0444 0.6847 1.0000
5.000 0.6106 0.04512 0.03492 -0.0410 0.6717 1.0000
5.250 0.6173 0.04660 0.03644 -0.0386 0.6589 1.0000
5.500 0.6371 0.04754 0.03747 -0.0373 0.6463 1.0000
5.750 0.6744 0.04756 0.03763 -0.0371 0.6337 1.0000
6.000 0.6910 0.04849 0.03866 -0.0353 0.6199 1.0000
6.250 0.6977 0.04994 0.04017 -0.0329 0.6049 1.0000
6.500 0.7185 0.05043 0.04078 -0.0310 0.5890 1.0000
6.750 0.7833 0.04706 0.03766 -0.0299 0.5706 1.0000
7.000 0.7803 0.04862 0.03928 -0.0263 0.5502 1.0000
7.250 0.8419 0.04405 0.03493 -0.0239 0.5276 1.0000
7.500 0.9007 0.03998 0.03102 -0.0221 0.5090 1.0000
7.750 0.9107 0.04047 0.03165 -0.0190 0.4878 1.0000
8.000 0.9622 0.03706 0.02832 -0.0172 0.4644 1.0000
8.250 0.9935 0.03545 0.02670 -0.0146 0.4341 1.0000
8.500 1.0188 0.03469 0.02581 -0.0118 0.3981 1.0000
8.750 1.0337 0.03520 0.02625 -0.0087 0.3617 1.0000
9.000 1.0496 0.03591 0.02685 -0.0060 0.3303 1.0000
9.250 1.0681 0.03665 0.02743 -0.0038 0.3052 1.0000
9.500 1.0812 0.03806 0.02889 -0.0015 0.2858 1.0000
9.750 1.0974 0.03952 0.03039 0.0003 0.2695 1.0000
10.000 1.1127 0.04102 0.03192 0.0021 0.2541 1.0000
10.250 1.1269 0.04252 0.03344 0.0040 0.2386 1.0000
10.500 1.1433 0.04319 0.03383 0.0058 0.2176 1.0000
10.750 1.1452 0.04466 0.03536 0.0087 0.2001 1.0000
11.000 1.1490 0.04645 0.03719 0.0114 0.1832 1.0000
11.250 1.1528 0.04866 0.03945 0.0139 0.1669 1.0000
11.500 1.1548 0.05130 0.04215 0.0164 0.1522 1.0000
11.750 1.1541 0.05429 0.04523 0.0189 0.1407 1.0000
12.000 0.8932 0.08950 0.08179 0.0079 0.2248 1.0000
12.250 0.8743 0.09748 0.08975 0.0052 0.2208 1.0000
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Polar data table (+)
Polar graphs
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