GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 534 AIRFOIL (goe534-il) Reynolds number: 200,000 Max Cl/Cd: 65.44 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe534-il-200000.txt Download as CSV file: xf-goe534-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2355 0.09247 0.08898 -0.0302 1.0000 0.0885
-8.500 -0.2367 0.09005 0.08663 -0.0302 1.0000 0.0903
-8.250 -0.4164 0.03298 0.02826 -0.0920 0.9703 0.0665
-8.000 -0.3850 0.02823 0.02275 -0.0975 0.9600 0.0691
-7.750 -0.3436 0.02759 0.02222 -0.1001 0.9538 0.0711
-7.500 -0.3081 0.02555 0.01983 -0.1027 0.9441 0.0742
-7.250 -0.2702 0.02358 0.01754 -0.1055 0.9361 0.0776
-7.000 -0.2357 0.02278 0.01671 -0.1067 0.9237 0.0812
-6.750 -0.2011 0.02143 0.01512 -0.1082 0.9119 0.0865
-6.500 -0.1653 0.02074 0.01426 -0.1095 0.8999 0.0926
-6.250 -0.1359 0.01982 0.01331 -0.1097 0.8842 0.0978
-6.000 -0.1067 0.01941 0.01264 -0.1095 0.8682 0.1037
-5.750 -0.0792 0.01865 0.01189 -0.1092 0.8527 0.1082
-5.500 -0.0515 0.01838 0.01147 -0.1087 0.8372 0.1131
-5.250 -0.0248 0.01786 0.01070 -0.1080 0.8218 0.1170
-5.000 0.0008 0.01742 0.01028 -0.1071 0.8053 0.1205
-4.750 0.0269 0.01715 0.00989 -0.1063 0.7892 0.1241
-4.500 0.0533 0.01698 0.00951 -0.1055 0.7733 0.1277
-4.250 0.0790 0.01648 0.00895 -0.1047 0.7578 0.1319
-4.000 0.1052 0.01631 0.00871 -0.1038 0.7416 0.1363
-3.750 0.1313 0.01606 0.00833 -0.1030 0.7246 0.1394
-3.500 0.1577 0.01582 0.00793 -0.1021 0.7079 0.1416
-3.250 0.1839 0.01536 0.00739 -0.1013 0.6919 0.1439
-3.000 0.2101 0.01502 0.00699 -0.1005 0.6762 0.1461
-2.750 0.2365 0.01477 0.00666 -0.0997 0.6606 0.1484
-2.500 0.2629 0.01453 0.00638 -0.0989 0.6442 0.1512
-2.250 0.2895 0.01434 0.00610 -0.0981 0.6286 0.1544
-2.000 0.3160 0.01414 0.00582 -0.0973 0.6138 0.1583
-1.750 0.3423 0.01396 0.00561 -0.0966 0.6001 0.1640
-1.500 0.3689 0.01384 0.00543 -0.0959 0.5861 0.1714
-1.250 0.3954 0.01368 0.00531 -0.0952 0.5734 0.1831
-1.000 0.4220 0.01355 0.00520 -0.0945 0.5622 0.2094
-0.750 0.4483 0.01340 0.00527 -0.0939 0.5503 0.2689
-0.500 0.4751 0.01352 0.00540 -0.0933 0.5400 0.3107
-0.250 0.5019 0.01368 0.00550 -0.0927 0.5293 0.3383
0.000 0.5288 0.01386 0.00563 -0.0920 0.5193 0.3596
0.250 0.5554 0.01401 0.00576 -0.0914 0.5093 0.3776
0.500 0.5821 0.01417 0.00592 -0.0908 0.5000 0.3937
0.750 0.6087 0.01430 0.00603 -0.0901 0.4905 0.4088
1.000 0.6353 0.01449 0.00618 -0.0895 0.4815 0.4256
1.250 0.6616 0.01461 0.00630 -0.0888 0.4718 0.4423
1.500 0.6881 0.01481 0.00643 -0.0882 0.4631 0.4592
1.750 0.7141 0.01489 0.00656 -0.0875 0.4537 0.4754
2.000 0.7404 0.01505 0.00668 -0.0868 0.4453 0.4914
2.250 0.7660 0.01510 0.00680 -0.0860 0.4355 0.5084
2.500 0.7919 0.01525 0.00689 -0.0854 0.4269 0.5264
2.750 0.8171 0.01527 0.00702 -0.0846 0.4171 0.5457
3.000 0.8430 0.01542 0.00711 -0.0839 0.4087 0.5677
3.250 0.8680 0.01541 0.00725 -0.0831 0.3987 0.5916
3.500 0.8932 0.01548 0.00733 -0.0824 0.3901 0.6208
3.750 0.9186 0.01534 0.00746 -0.0817 0.3801 0.6744
4.000 0.9639 0.01515 0.00760 -0.0850 0.3695 1.0000
4.250 0.9894 0.01538 0.00777 -0.0844 0.3599 1.0000
4.500 1.0146 0.01572 0.00798 -0.0837 0.3514 1.0000
4.750 1.0393 0.01598 0.00820 -0.0830 0.3425 1.0000
5.000 1.0641 0.01637 0.00845 -0.0822 0.3348 1.0000
5.250 1.0882 0.01664 0.00873 -0.0814 0.3262 1.0000
5.750 1.1364 0.01737 0.00933 -0.0798 0.3114 1.0000
6.000 1.1602 0.01773 0.00961 -0.0789 0.3046 1.0000
6.250 1.1839 0.01817 0.01001 -0.0781 0.2981 1.0000
6.500 1.2071 0.01851 0.01037 -0.0772 0.2913 1.0000
6.750 1.2308 0.01900 0.01072 -0.0764 0.2856 1.0000
7.000 1.2534 0.01942 0.01120 -0.0755 0.2797 1.0000
7.250 1.2758 0.01981 0.01159 -0.0745 0.2738 1.0000
7.500 1.2992 0.02037 0.01201 -0.0737 0.2684 1.0000
7.750 1.3204 0.02080 0.01254 -0.0726 0.2631 1.0000
8.000 1.3418 0.02124 0.01300 -0.0715 0.2577 1.0000
8.250 1.3641 0.02178 0.01344 -0.0707 0.2527 1.0000
8.500 1.3846 0.02233 0.01405 -0.0695 0.2477 1.0000
8.750 1.4042 0.02280 0.01458 -0.0682 0.2426 1.0000
9.000 1.4246 0.02332 0.01505 -0.0671 0.2379 1.0000
9.250 1.4452 0.02401 0.01572 -0.0661 0.2332 1.0000
9.500 1.4618 0.02452 0.01634 -0.0644 0.2283 1.0000
9.750 1.4795 0.02504 0.01686 -0.0629 0.2237 1.0000
10.000 1.5015 0.02584 0.01752 -0.0623 0.2189 1.0000
10.250 1.5132 0.02639 0.01825 -0.0599 0.2148 1.0000
10.500 1.5263 0.02696 0.01890 -0.0579 0.2104 1.0000
10.750 1.5400 0.02756 0.01947 -0.0559 0.2063 1.0000
11.000 1.5564 0.02842 0.02029 -0.0545 0.2023 1.0000
11.250 1.5622 0.02913 0.02117 -0.0516 0.1985 1.0000
11.500 1.5713 0.02987 0.02196 -0.0493 0.1946 1.0000
11.750 1.5833 0.03064 0.02271 -0.0475 0.1910 1.0000
12.000 1.5967 0.03165 0.02371 -0.0461 0.1873 1.0000
12.250 1.5993 0.03272 0.02496 -0.0436 0.1838 1.0000
12.500 1.6053 0.03377 0.02609 -0.0416 0.1802 1.0000
12.750 1.6141 0.03480 0.02712 -0.0401 0.1770 1.0000
13.000 1.6276 0.03594 0.02821 -0.0390 0.1734 1.0000
13.250 1.6262 0.03757 0.03005 -0.0371 0.1706 1.0000
13.500 1.6287 0.03915 0.03174 -0.0357 0.1673 1.0000
13.750 1.6344 0.04059 0.03322 -0.0346 0.1643 1.0000
14.000 1.6466 0.04180 0.03435 -0.0338 0.1613 1.0000
14.250 1.6464 0.04390 0.03660 -0.0328 0.1585 1.0000
14.500 1.6427 0.04628 0.03916 -0.0320 0.1557 1.0000
14.750 1.6431 0.04842 0.04140 -0.0314 0.1529 1.0000
15.000 1.6476 0.05026 0.04325 -0.0309 0.1502 1.0000
15.250 1.6627 0.05141 0.04429 -0.0302 0.1472 1.0000
15.500 1.6498 0.05499 0.04812 -0.0301 0.1451 1.0000
15.750 1.6416 0.05834 0.05166 -0.0303 0.1427 1.0000
16.000 1.6385 0.06128 0.05469 -0.0304 0.1402 1.0000
16.250 1.6420 0.06354 0.05698 -0.0305 0.1380 1.0000
16.500 1.6584 0.06444 0.05777 -0.0298 0.1354 1.0000
16.750 1.6446 0.06889 0.06243 -0.0307 0.1336 1.0000
17.000 1.6258 0.07418 0.06797 -0.0323 0.1318 1.0000
17.250 1.6113 0.07917 0.07314 -0.0339 0.1298 1.0000
17.500 1.6044 0.08325 0.07733 -0.0351 0.1278 1.0000
17.750 1.6093 0.08565 0.07974 -0.0356 0.1259 1.0000
18.000 1.6302 0.08575 0.07973 -0.0346 0.1239 1.0000
18.250 1.6071 0.09235 0.08655 -0.0373 0.1224 1.0000
18.500 1.5564 0.10367 0.09824 -0.0429 0.1210 1.0000
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Polar data table (+)
Polar graphs
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