GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 534 AIRFOIL (goe534-il) Reynolds number: 100,000 Max Cl/Cd: 44.03 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe534-il-100000.txt Download as CSV file: xf-goe534-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 534 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2184 0.10543 0.10037 -0.0262 1.0000 0.1357
-9.000 -0.2360 0.10467 0.09972 -0.0285 1.0000 0.1412
-8.750 -0.2518 0.10245 0.09763 -0.0300 1.0000 0.1429
-8.500 -0.2184 0.09833 0.09351 -0.0268 1.0000 0.1457
-8.250 -0.2106 0.09621 0.09146 -0.0256 1.0000 0.1497
-8.000 -0.2245 0.09518 0.09058 -0.0256 1.0000 0.1548
-7.750 -0.2783 0.09707 0.09274 -0.0228 1.0000 0.1564
-7.500 -0.3179 0.09835 0.09419 -0.0167 1.0000 0.1565
-7.250 -0.3037 0.09412 0.09001 -0.0169 0.9970 0.1584
-7.000 -0.2549 0.08969 0.08555 -0.0185 0.9930 0.1629
-6.750 -0.2436 0.08483 0.08068 -0.0370 0.9708 0.1734
-6.500 -0.2001 0.08133 0.07718 -0.0332 0.9682 0.1775
-6.250 -0.1735 0.07603 0.07183 -0.0496 0.9515 0.1904
-6.000 -0.1386 0.07270 0.06851 -0.0476 0.9420 0.1939
-5.750 -0.1154 0.05924 0.05475 -0.0756 0.9238 0.1735
-5.500 -0.0742 0.05673 0.05226 -0.0758 0.9173 0.1765
-5.250 -0.0410 0.05559 0.05112 -0.0762 0.9030 0.1951
-5.000 -0.0263 0.02869 0.02175 -0.1072 0.8852 0.1575
-4.750 0.0096 0.02842 0.02176 -0.1076 0.8709 0.1651
-4.500 0.0440 0.02676 0.01960 -0.1091 0.8567 0.1738
-4.250 0.0774 0.02612 0.01904 -0.1092 0.8420 0.1797
-4.000 0.1048 0.02499 0.01763 -0.1088 0.8242 0.1833
-3.750 0.1318 0.02396 0.01623 -0.1082 0.8067 0.1867
-3.500 0.1587 0.02309 0.01502 -0.1075 0.7895 0.1898
-3.250 0.1853 0.02238 0.01424 -0.1067 0.7731 0.1928
-3.000 0.2128 0.02186 0.01357 -0.1059 0.7578 0.1965
-2.750 0.2396 0.02141 0.01293 -0.1050 0.7422 0.2015
-2.500 0.2655 0.02103 0.01233 -0.1041 0.7259 0.2068
-2.250 0.2913 0.02064 0.01199 -0.1031 0.7111 0.2124
-2.000 0.3190 0.02031 0.01151 -0.1023 0.6983 0.2203
-1.750 0.3446 0.01998 0.01118 -0.1013 0.6836 0.2296
-1.500 0.3705 0.01975 0.01094 -0.1004 0.6697 0.2448
-1.250 0.3974 0.01952 0.01077 -0.0994 0.6578 0.2690
-1.000 0.4225 0.01940 0.01079 -0.0983 0.6442 0.3096
-0.750 0.4474 0.01952 0.01099 -0.0970 0.6313 0.3516
-0.500 0.4745 0.01963 0.01099 -0.0960 0.6207 0.3838
-0.250 0.4987 0.01981 0.01123 -0.0948 0.6073 0.4078
0.000 0.5245 0.01996 0.01133 -0.0938 0.5959 0.4302
0.250 0.5510 0.02004 0.01133 -0.0928 0.5849 0.4513
0.500 0.5760 0.02020 0.01149 -0.0919 0.5729 0.4717
0.750 0.6036 0.02030 0.01142 -0.0911 0.5633 0.4959
1.000 0.6271 0.02042 0.01165 -0.0899 0.5509 0.5176
1.250 0.6530 0.02049 0.01169 -0.0890 0.5407 0.5403
1.500 0.6778 0.02054 0.01175 -0.0880 0.5293 0.5638
1.750 0.7029 0.02066 0.01186 -0.0871 0.5187 0.5873
2.000 0.7308 0.02068 0.01182 -0.0866 0.5081 0.6109
2.250 0.7572 0.02079 0.01200 -0.0861 0.4966 0.6355
2.500 0.7869 0.02077 0.01191 -0.0860 0.4868 0.6669
2.750 0.8116 0.02073 0.01218 -0.0853 0.4751 0.7123
3.000 0.8548 0.02052 0.01222 -0.0879 0.4640 1.0000
3.250 0.8818 0.02094 0.01252 -0.0877 0.4525 1.0000
3.500 0.9087 0.02142 0.01282 -0.0874 0.4426 1.0000
3.750 0.9348 0.02182 0.01309 -0.0868 0.4325 1.0000
4.000 0.9600 0.02234 0.01350 -0.0862 0.4230 1.0000
4.250 0.9855 0.02273 0.01377 -0.0855 0.4134 1.0000
4.500 1.0101 0.02327 0.01424 -0.0848 0.4044 1.0000
4.750 1.0348 0.02371 0.01461 -0.0840 0.3954 1.0000
5.000 1.0599 0.02425 0.01505 -0.0834 0.3875 1.0000
5.250 1.0827 0.02476 0.01557 -0.0824 0.3786 1.0000
5.500 1.1105 0.02522 0.01581 -0.0821 0.3718 1.0000
5.750 1.1298 0.02591 0.01666 -0.0807 0.3629 1.0000
6.000 1.1568 0.02629 0.01686 -0.0803 0.3562 1.0000
6.250 1.1770 0.02707 0.01774 -0.0791 0.3486 1.0000
6.500 1.2002 0.02759 0.01824 -0.0782 0.3415 1.0000
6.750 1.2273 0.02814 0.01862 -0.0779 0.3356 1.0000
7.000 1.2438 0.02900 0.01969 -0.0762 0.3279 1.0000
7.250 1.2693 0.02944 0.02003 -0.0757 0.3219 1.0000
7.500 1.2907 0.03029 0.02089 -0.0747 0.3158 1.0000
7.750 1.3082 0.03113 0.02187 -0.0733 0.3091 1.0000
8.000 1.3353 0.03156 0.02214 -0.0729 0.3036 1.0000
8.250 1.3521 0.03265 0.02335 -0.0715 0.2976 1.0000
8.500 1.3686 0.03353 0.02436 -0.0700 0.2914 1.0000
8.750 1.3969 0.03395 0.02459 -0.0698 0.2861 1.0000
9.000 1.4097 0.03525 0.02607 -0.0680 0.2805 1.0000
9.250 1.4234 0.03628 0.02725 -0.0663 0.2746 1.0000
9.500 1.4517 0.03668 0.02749 -0.0662 0.2694 1.0000
9.750 1.4622 0.03812 0.02910 -0.0642 0.2643 1.0000
10.000 1.4703 0.03945 0.03061 -0.0620 0.2588 1.0000
10.250 1.4960 0.03990 0.03095 -0.0616 0.2537 1.0000
10.500 1.5100 0.04125 0.03236 -0.0601 0.2489 1.0000
10.750 1.5073 0.04306 0.03445 -0.0569 0.2440 1.0000
11.000 1.5228 0.04392 0.03532 -0.0555 0.2392 1.0000
11.250 1.5565 0.04450 0.03570 -0.0562 0.2342 1.0000
11.500 1.5345 0.04706 0.03865 -0.0513 0.2306 1.0000
11.750 1.5210 0.04918 0.04096 -0.0473 0.2269 1.0000
12.000 1.5356 0.05002 0.04179 -0.0460 0.2227 1.0000
12.250 1.5687 0.05070 0.04232 -0.0465 0.2180 1.0000
12.500 1.5212 0.05471 0.04671 -0.0411 0.2161 1.0000
12.750 1.4470 0.06228 0.05470 -0.0383 0.2146 1.0000
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Polar data table (+)
Polar graphs
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