GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 484 AIRFOIL (goe484-il) Reynolds number: 100,000 Max Cl/Cd: 65.4 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe484-il-100000-n5.txt Download as CSV file: xf-goe484-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 484 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3667 0.10203 0.09715 -0.0263 1.0000 0.0557
-7.500 -0.3852 0.10199 0.09721 -0.0242 1.0000 0.0563
-7.250 -0.3974 0.10134 0.09666 -0.0257 1.0000 0.0567
-7.000 -0.3920 0.09894 0.09428 -0.0317 0.9984 0.0570
-6.750 -0.3876 0.09384 0.08921 -0.0242 0.9983 0.0583
-6.500 -0.3711 0.09024 0.08560 -0.0251 0.9954 0.0600
-6.250 -0.3523 0.08672 0.08206 -0.0288 0.9912 0.0623
-6.000 -0.3267 0.08286 0.07814 -0.0363 0.9862 0.0662
-5.750 -0.2837 0.07732 0.07247 -0.0547 0.9781 0.0700
-5.500 -0.2713 0.07402 0.06920 -0.0513 0.9739 0.0721
-5.250 -0.2437 0.07037 0.06551 -0.0555 0.9684 0.0749
-5.000 -0.2127 0.06650 0.06155 -0.0622 0.9618 0.0785
-4.750 -0.1423 0.06045 0.05503 -0.0844 0.9566 0.0835
-4.500 -0.1336 0.05700 0.05169 -0.0818 0.9513 0.0848
-4.000 -0.0489 0.04455 0.03863 -0.0971 0.9448 0.0555
-3.750 -0.0218 0.04140 0.03533 -0.0996 0.9390 0.0536
-3.500 0.0178 0.03726 0.03087 -0.1047 0.9355 0.0514
-3.000 0.0911 0.03072 0.02352 -0.1117 0.9276 0.0521
-2.750 0.1272 0.02794 0.02027 -0.1142 0.9238 0.0515
-2.500 0.1654 0.02551 0.01733 -0.1168 0.9210 0.0507
-2.250 0.1986 0.02377 0.01516 -0.1180 0.9169 0.0505
-2.000 0.2285 0.02252 0.01359 -0.1185 0.9113 0.0506
-1.750 0.2639 0.02140 0.01221 -0.1199 0.9078 0.0511
-1.500 0.3005 0.02045 0.01107 -0.1215 0.9048 0.0519
-1.250 0.3253 0.01994 0.01047 -0.1209 0.8970 0.0539
-1.000 0.3604 0.01933 0.00975 -0.1221 0.8931 0.0566
-0.750 0.3966 0.01862 0.00903 -0.1236 0.8899 0.0582
-0.500 0.4215 0.01825 0.00869 -0.1229 0.8814 0.0598
-0.250 0.4576 0.01778 0.00822 -0.1243 0.8772 0.0625
0.000 0.4867 0.01750 0.00792 -0.1244 0.8702 0.0663
0.250 0.5184 0.01717 0.00765 -0.1249 0.8640 0.0739
0.500 0.5566 0.01675 0.00738 -0.1266 0.8601 0.1101
0.750 0.5829 0.01655 0.00741 -0.1262 0.8504 0.1899
1.000 0.6186 0.01535 0.00742 -0.1280 0.8458 0.5793
1.500 0.6825 0.01464 0.00715 -0.1287 0.8305 1.0000
1.750 0.7092 0.01472 0.00718 -0.1283 0.8200 1.0000
2.000 0.7439 0.01464 0.00706 -0.1292 0.8133 1.0000
2.250 0.7699 0.01476 0.00718 -0.1286 0.8020 1.0000
2.500 0.7982 0.01480 0.00722 -0.1283 0.7903 1.0000
2.750 0.8269 0.01475 0.00717 -0.1280 0.7758 1.0000
3.000 0.8562 0.01455 0.00694 -0.1274 0.7539 1.0000
3.250 0.8804 0.01438 0.00669 -0.1257 0.7181 1.0000
3.500 0.9080 0.01426 0.00637 -0.1246 0.6746 1.0000
3.750 0.9354 0.01437 0.00625 -0.1236 0.6306 1.0000
4.000 0.9601 0.01468 0.00640 -0.1225 0.5957 1.0000
4.250 0.9823 0.01510 0.00665 -0.1210 0.5545 1.0000
4.500 1.0015 0.01560 0.00697 -0.1190 0.4984 1.0000
4.750 1.0122 0.01667 0.00734 -0.1156 0.3596 1.0000
5.000 1.0172 0.01873 0.00833 -0.1121 0.1977 1.0000
5.250 1.0249 0.02073 0.00948 -0.1091 0.0886 1.0000
5.500 1.0429 0.02164 0.01034 -0.1074 0.0774 1.0000
5.750 1.0614 0.02245 0.01121 -0.1057 0.0724 1.0000
6.000 1.0796 0.02326 0.01214 -0.1040 0.0688 1.0000
6.250 1.0964 0.02416 0.01313 -0.1022 0.0659 1.0000
6.500 1.1109 0.02526 0.01427 -0.1000 0.0631 1.0000
6.750 1.1258 0.02633 0.01541 -0.0979 0.0605 1.0000
7.000 1.1424 0.02731 0.01652 -0.0961 0.0578 1.0000
7.250 1.1588 0.02845 0.01775 -0.0942 0.0559 1.0000
7.500 1.1765 0.02969 0.01904 -0.0927 0.0538 1.0000
7.750 1.1951 0.03109 0.02041 -0.0914 0.0510 1.0000
8.000 1.2192 0.03305 0.02235 -0.0911 0.0482 1.0000
8.250 1.2432 0.03447 0.02399 -0.0904 0.0463 1.0000
8.500 1.2655 0.03592 0.02563 -0.0896 0.0434 1.0000
8.750 1.2869 0.03753 0.02738 -0.0888 0.0408 1.0000
9.000 1.3100 0.03960 0.02952 -0.0884 0.0388 1.0000
9.250 1.3323 0.04234 0.03244 -0.0880 0.0366 1.0000
9.500 1.3467 0.04415 0.03469 -0.0860 0.0345 1.0000
9.750 1.3615 0.04669 0.03761 -0.0842 0.0330 1.0000
10.000 1.3729 0.04912 0.04035 -0.0822 0.0316 1.0000
10.250 1.3824 0.05119 0.04261 -0.0802 0.0302 1.0000
10.500 1.3900 0.05329 0.04483 -0.0782 0.0289 1.0000
10.750 1.3930 0.05657 0.04833 -0.0759 0.0279 1.0000
11.000 1.3848 0.05937 0.05159 -0.0716 0.0274 1.0000
11.250 1.3740 0.06256 0.05516 -0.0676 0.0270 1.0000
11.500 1.3602 0.06598 0.05895 -0.0640 0.0267 1.0000
11.750 1.3441 0.06970 0.06300 -0.0609 0.0265 1.0000
12.000 1.3262 0.07376 0.06737 -0.0586 0.0263 1.0000
12.250 1.3064 0.07825 0.07214 -0.0572 0.0262 1.0000
12.500 1.2856 0.08321 0.07736 -0.0567 0.0262 1.0000
12.750 1.2632 0.08878 0.08317 -0.0573 0.0262 1.0000
13.000 1.2403 0.09498 0.08959 -0.0590 0.0262 1.0000
13.250 1.2169 0.10197 0.09678 -0.0620 0.0264 1.0000
13.500 1.1931 0.10982 0.10480 -0.0663 0.0266 1.0000
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Polar data table (+)
Polar graphs
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