GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 573 AIRFOIL (goe573-il) Reynolds number: 200,000 Max Cl/Cd: 69.66 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe573-il-200000-n5.txt Download as CSV file: xf-goe573-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 573 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0229 0.09189 0.08775 -0.1059 0.8207 0.0309
-9.750 0.0345 0.08782 0.08354 -0.1133 0.7928 0.0318
-9.250 0.0461 0.08119 0.07667 -0.1188 0.7460 0.0320
-9.000 0.0489 0.07811 0.07351 -0.1202 0.7279 0.0320
-8.750 0.0479 0.07496 0.07029 -0.1220 0.7121 0.0321
-8.250 0.0591 0.06988 0.06506 -0.1209 0.6838 0.0315
-8.000 0.0619 0.06745 0.06257 -0.1203 0.6720 0.0306
-7.750 0.0573 0.06480 0.05989 -0.1201 0.6616 0.0298
-7.500 0.0513 0.06215 0.05720 -0.1197 0.6530 0.0293
-7.250 0.0485 0.05905 0.05403 -0.1199 0.6443 0.0289
-7.000 0.0489 0.05604 0.05094 -0.1202 0.6360 0.0299
-6.750 0.0501 0.05278 0.04756 -0.1201 0.6284 0.0303
-6.500 0.0521 0.04907 0.04368 -0.1198 0.6216 0.0309
-6.250 0.0564 0.04573 0.04017 -0.1188 0.6145 0.0309
-6.000 0.0607 0.04199 0.03618 -0.1172 0.6086 0.0312
-5.750 0.0621 0.03734 0.03112 -0.1145 0.6029 0.0326
-5.500 0.0780 0.03685 0.03059 -0.1134 0.5953 0.0334
-5.250 0.0926 0.03555 0.02917 -0.1119 0.5882 0.0343
-5.000 0.1042 0.03323 0.02658 -0.1096 0.5818 0.0346
-4.750 0.1166 0.03094 0.02398 -0.1073 0.5758 0.0349
-4.500 0.1317 0.02923 0.02202 -0.1052 0.5690 0.0360
-4.250 0.1468 0.02738 0.01982 -0.1029 0.5631 0.0373
-4.000 0.1628 0.02552 0.01762 -0.1006 0.5566 0.0376
-3.750 0.1804 0.02392 0.01567 -0.0985 0.5503 0.0381
-3.500 0.1998 0.02264 0.01403 -0.0967 0.5447 0.0386
-3.250 0.2211 0.02179 0.01285 -0.0952 0.5385 0.0397
-3.000 0.2425 0.02082 0.01159 -0.0939 0.5330 0.0404
-2.750 0.2652 0.01985 0.01044 -0.0929 0.5278 0.0409
-2.500 0.2887 0.01913 0.00957 -0.0920 0.5221 0.0414
-2.250 0.3125 0.01858 0.00888 -0.0912 0.5172 0.0421
-2.000 0.3369 0.01809 0.00828 -0.0905 0.5124 0.0427
-1.750 0.3613 0.01768 0.00779 -0.0898 0.5071 0.0437
-1.500 0.3854 0.01739 0.00740 -0.0890 0.5025 0.0452
-1.250 0.4097 0.01708 0.00699 -0.0883 0.4983 0.0466
-1.000 0.4341 0.01674 0.00660 -0.0876 0.4937 0.0474
-0.750 0.4580 0.01647 0.00627 -0.0868 0.4897 0.0482
-0.500 0.4815 0.01626 0.00599 -0.0859 0.4862 0.0491
-0.250 0.5050 0.01611 0.00576 -0.0850 0.4830 0.0500
0.000 0.5276 0.01585 0.00553 -0.0840 0.4795 0.0517
0.250 0.5504 0.01571 0.00539 -0.0831 0.4760 0.0544
0.500 0.5737 0.01566 0.00530 -0.0822 0.4729 0.0582
0.750 0.5972 0.01565 0.00520 -0.0814 0.4701 0.0618
1.000 0.6205 0.01559 0.00513 -0.0805 0.4672 0.0679
1.250 0.6434 0.01554 0.00514 -0.0796 0.4640 0.0820
1.500 0.6652 0.01541 0.00518 -0.0785 0.4609 0.1467
1.750 0.8800 0.01451 0.00600 -0.1197 0.4549 1.0000
2.000 0.9029 0.01470 0.00607 -0.1188 0.4528 1.0000
2.250 0.9253 0.01485 0.00620 -0.1179 0.4504 1.0000
2.500 0.9474 0.01502 0.00635 -0.1169 0.4478 1.0000
2.750 0.9693 0.01518 0.00649 -0.1158 0.4451 1.0000
3.000 0.9912 0.01536 0.00663 -0.1148 0.4427 1.0000
3.250 1.0133 0.01555 0.00678 -0.1138 0.4404 1.0000
3.500 1.0359 0.01575 0.00693 -0.1130 0.4385 1.0000
3.750 1.0590 0.01599 0.00710 -0.1123 0.4367 1.0000
4.000 1.0798 0.01618 0.00734 -0.1111 0.4344 1.0000
4.250 1.1006 0.01638 0.00758 -0.1099 0.4319 1.0000
4.500 1.1216 0.01660 0.00781 -0.1087 0.4295 1.0000
4.750 1.1426 0.01681 0.00804 -0.1076 0.4273 1.0000
5.000 1.1636 0.01703 0.00826 -0.1064 0.4250 1.0000
5.250 1.1851 0.01726 0.00844 -0.1054 0.4224 1.0000
5.500 1.2045 0.01749 0.00871 -0.1040 0.4193 1.0000
5.750 1.2217 0.01770 0.00899 -0.1021 0.4158 1.0000
6.000 1.2399 0.01792 0.00925 -0.1005 0.4126 1.0000
6.250 1.2590 0.01815 0.00951 -0.0990 0.4100 1.0000
6.500 1.2791 0.01840 0.00978 -0.0978 0.4079 1.0000
6.750 1.3006 0.01867 0.01004 -0.0969 0.4059 1.0000
7.000 1.3173 0.01895 0.01041 -0.0950 0.4034 1.0000
7.250 1.3333 0.01923 0.01081 -0.0930 0.4007 1.0000
7.500 1.3499 0.01951 0.01117 -0.0912 0.3982 1.0000
7.750 1.3668 0.01979 0.01152 -0.0894 0.3958 1.0000
8.000 1.3841 0.02008 0.01186 -0.0877 0.3935 1.0000
8.250 1.4029 0.02036 0.01217 -0.0863 0.3914 1.0000
8.500 1.4157 0.02065 0.01255 -0.0838 0.3880 1.0000
8.750 1.4196 0.02089 0.01291 -0.0795 0.3834 1.0000
9.000 1.4248 0.02105 0.01312 -0.0754 0.3781 1.0000
9.250 1.4330 0.02128 0.01336 -0.0720 0.3732 1.0000
9.500 1.4363 0.02161 0.01384 -0.0680 0.3672 1.0000
9.750 1.4449 0.02193 0.01421 -0.0649 0.3623 1.0000
10.000 1.4526 0.02233 0.01470 -0.0619 0.3571 1.0000
10.250 1.4562 0.02282 0.01529 -0.0583 0.3493 1.0000
10.500 1.4597 0.02340 0.01594 -0.0549 0.3411 1.0000
10.750 1.4636 0.02409 0.01670 -0.0519 0.3330 1.0000
11.000 1.4671 0.02493 0.01764 -0.0490 0.3237 1.0000
11.250 1.4677 0.02598 0.01876 -0.0460 0.3122 1.0000
11.500 1.4607 0.02755 0.02031 -0.0426 0.2932 1.0000
11.750 1.4529 0.02946 0.02219 -0.0396 0.2766 1.0000
12.000 1.4418 0.03187 0.02456 -0.0368 0.2607 1.0000
12.250 1.4232 0.03514 0.02777 -0.0341 0.2409 1.0000
12.500 1.4061 0.03861 0.03122 -0.0319 0.2252 1.0000
12.750 1.3861 0.04264 0.03522 -0.0302 0.2089 1.0000
13.000 1.3690 0.04661 0.03920 -0.0289 0.1945 1.0000
13.250 1.3442 0.05159 0.04413 -0.0278 0.1729 1.0000
13.500 1.3158 0.05720 0.04966 -0.0269 0.1460 1.0000
13.750 1.2895 0.06282 0.05520 -0.0264 0.1246 1.0000
14.000 1.2614 0.06886 0.06114 -0.0261 0.1025 1.0000
14.250 1.2381 0.07451 0.06671 -0.0261 0.0775 1.0000
14.500 1.2131 0.08053 0.07263 -0.0262 0.0543 1.0000
14.750 1.1919 0.08624 0.07828 -0.0265 0.0364 1.0000
15.000 1.1795 0.09094 0.08299 -0.0269 0.0286 1.0000
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