GOE 409 AIRFOIL (goe409-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 409 AIRFOIL (goe409-il) Reynolds number: 200,000 Max Cl/Cd: 40.85 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe409-il-200000.txt Download as CSV file: xf-goe409-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 409 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7160 0.09697 0.09307 -0.0392 1.0000 0.0781
-13.000 -0.6954 0.09645 0.09256 -0.0360 1.0000 0.0790
-12.750 -0.9504 0.05504 0.04995 -0.0536 1.0000 0.0483
-12.500 -0.9580 0.05291 0.04771 -0.0517 1.0000 0.0495
-12.250 -0.9746 0.05033 0.04493 -0.0486 1.0000 0.0500
-12.000 -0.9889 0.04855 0.04296 -0.0446 1.0000 0.0513
-11.750 -1.0062 0.04668 0.04085 -0.0394 1.0000 0.0523
-11.500 -1.0193 0.04546 0.03931 -0.0343 1.0000 0.0536
-11.250 -1.0314 0.04475 0.03826 -0.0289 1.0000 0.0546
-11.000 -1.0257 0.04023 0.03369 -0.0276 1.0000 0.0569
-10.750 -1.0104 0.03892 0.03242 -0.0263 1.0000 0.0591
-10.500 -1.0048 0.03771 0.03107 -0.0232 1.0000 0.0614
-10.250 -1.0021 0.03657 0.02967 -0.0195 1.0000 0.0632
-10.000 -1.0000 0.03608 0.02890 -0.0152 1.0000 0.0648
-9.750 -0.9947 0.03324 0.02580 -0.0123 1.0000 0.0667
-9.500 -0.9796 0.03141 0.02397 -0.0109 1.0000 0.0690
-9.250 -0.9657 0.03031 0.02282 -0.0088 1.0000 0.0711
-9.000 -0.9528 0.02933 0.02172 -0.0064 1.0000 0.0732
-8.750 -0.9399 0.02844 0.02065 -0.0039 1.0000 0.0750
-8.500 -0.9268 0.02774 0.01976 -0.0014 1.0000 0.0765
-8.250 -0.9126 0.02709 0.01893 0.0010 1.0000 0.0773
-8.000 -0.8912 0.02504 0.01679 0.0018 1.0000 0.0787
-7.750 -0.8708 0.02374 0.01546 0.0029 1.0000 0.0802
-7.500 -0.8517 0.02280 0.01450 0.0043 1.0000 0.0812
-7.250 -0.8334 0.02200 0.01366 0.0060 1.0000 0.0821
-7.000 -0.8157 0.02126 0.01290 0.0077 1.0000 0.0832
-6.750 -0.7987 0.02061 0.01222 0.0096 1.0000 0.0844
-6.500 -0.7823 0.02001 0.01159 0.0115 1.0000 0.0858
-6.250 -0.7661 0.01945 0.01100 0.0136 1.0000 0.0869
-6.000 -0.7503 0.01892 0.01043 0.0156 1.0000 0.0879
-5.750 -0.7346 0.01844 0.00991 0.0177 1.0000 0.0889
-5.500 -0.7190 0.01799 0.00942 0.0198 1.0000 0.0898
-5.250 -0.7049 0.01742 0.00887 0.0221 1.0000 0.0914
-5.000 -0.6903 0.01692 0.00839 0.0243 1.0000 0.0934
-4.750 -0.6747 0.01652 0.00799 0.0263 1.0000 0.0963
-4.500 -0.6525 0.01619 0.00765 0.0270 0.9988 0.1001
-4.250 -0.6154 0.01588 0.00741 0.0246 0.9943 0.1076
-4.000 -0.5810 0.01548 0.00718 0.0228 0.9892 0.1290
-3.750 -0.5464 0.01486 0.00695 0.0208 0.9841 0.1980
-3.500 -0.5187 0.01396 0.00667 0.0200 0.9777 0.3121
-3.250 -0.4888 0.01328 0.00665 0.0190 0.9718 0.4526
-3.000 -0.4586 0.01301 0.00663 0.0183 0.9652 0.5186
-2.750 -0.4243 0.01279 0.00662 0.0169 0.9592 0.5670
-2.500 -0.3896 0.01261 0.00662 0.0156 0.9534 0.6093
-2.250 -0.3577 0.01243 0.00662 0.0149 0.9461 0.6526
-2.000 -0.3167 0.01231 0.00665 0.0125 0.9423 0.6917
-1.750 -0.2891 0.01221 0.00668 0.0129 0.9333 0.7260
-1.500 -0.2474 0.01213 0.00674 0.0106 0.9288 0.7619
-1.250 -0.2119 0.01213 0.00685 0.0096 0.9221 0.7922
-1.000 -0.1729 0.01219 0.00698 0.0080 0.9159 0.8200
-0.750 -0.1264 0.01232 0.00716 0.0051 0.9126 0.8460
-0.500 -0.0916 0.01252 0.00741 0.0048 0.9039 0.8656
-0.250 -0.0457 0.01266 0.00756 0.0024 0.8981 0.8809
0.000 0.0000 0.01275 0.00766 0.0000 0.8895 0.8896
0.250 0.0455 0.01267 0.00757 -0.0024 0.8810 0.8981
0.500 0.0913 0.01252 0.00741 -0.0048 0.8658 0.9039
0.750 0.1262 0.01232 0.00716 -0.0051 0.8457 0.9126
1.000 0.1729 0.01219 0.00698 -0.0080 0.8200 0.9160
1.250 0.2118 0.01213 0.00684 -0.0095 0.7922 0.9221
1.500 0.2473 0.01213 0.00674 -0.0105 0.7617 0.9288
1.750 0.2892 0.01220 0.00669 -0.0129 0.7270 0.9333
2.000 0.3167 0.01231 0.00665 -0.0125 0.6917 0.9423
2.250 0.3577 0.01243 0.00662 -0.0149 0.6527 0.9461
2.500 0.3895 0.01261 0.00662 -0.0156 0.6095 0.9534
2.750 0.4240 0.01278 0.00661 -0.0169 0.5670 0.9592
3.000 0.4586 0.01300 0.00663 -0.0183 0.5198 0.9653
3.250 0.4887 0.01329 0.00664 -0.0189 0.4495 0.9719
3.500 0.5186 0.01394 0.00666 -0.0200 0.3146 0.9777
3.750 0.5465 0.01485 0.00694 -0.0208 0.1989 0.9841
4.000 0.5811 0.01547 0.00717 -0.0229 0.1295 0.9892
4.250 0.6154 0.01587 0.00740 -0.0246 0.1078 0.9943
4.500 0.6526 0.01619 0.00765 -0.0270 0.1001 0.9989
4.750 0.6745 0.01651 0.00799 -0.0263 0.0962 1.0000
5.000 0.6901 0.01692 0.00839 -0.0243 0.0934 1.0000
5.250 0.7046 0.01742 0.00887 -0.0221 0.0914 1.0000
5.500 0.7188 0.01799 0.00942 -0.0198 0.0898 1.0000
5.750 0.7345 0.01843 0.00990 -0.0177 0.0889 1.0000
6.000 0.7501 0.01891 0.01042 -0.0156 0.0879 1.0000
6.250 0.7659 0.01945 0.01099 -0.0135 0.0870 1.0000
6.500 0.7821 0.02001 0.01159 -0.0115 0.0858 1.0000
6.750 0.7986 0.02060 0.01221 -0.0096 0.0845 1.0000
7.000 0.8155 0.02125 0.01289 -0.0077 0.0831 1.0000
7.250 0.8332 0.02198 0.01365 -0.0059 0.0821 1.0000
7.500 0.8516 0.02279 0.01449 -0.0043 0.0812 1.0000
7.750 0.8706 0.02372 0.01545 -0.0029 0.0802 1.0000
8.000 0.8909 0.02498 0.01673 -0.0017 0.0788 1.0000
8.250 0.9126 0.02710 0.01894 -0.0010 0.0773 1.0000
8.500 0.9266 0.02771 0.01973 0.0014 0.0765 1.0000
8.750 0.9397 0.02843 0.02064 0.0040 0.0750 1.0000
9.000 0.9526 0.02933 0.02172 0.0065 0.0732 1.0000
9.250 0.9656 0.03030 0.02281 0.0088 0.0711 1.0000
9.500 0.9795 0.03140 0.02396 0.0109 0.0689 1.0000
9.750 0.9948 0.03331 0.02586 0.0123 0.0665 1.0000
10.000 0.9999 0.03606 0.02888 0.0153 0.0648 1.0000
10.250 1.0020 0.03659 0.02969 0.0195 0.0633 1.0000
10.500 1.0048 0.03771 0.03106 0.0232 0.0613 1.0000
10.750 1.0104 0.03893 0.03243 0.0263 0.0591 1.0000
11.000 1.0257 0.04025 0.03372 0.0276 0.0570 1.0000
11.500 1.0185 0.04537 0.03923 0.0345 0.0535 1.0000
11.750 1.0059 0.04674 0.04091 0.0395 0.0522 1.0000
12.000 0.9896 0.04849 0.04290 0.0445 0.0512 1.0000
12.250 0.9744 0.05044 0.04505 0.0486 0.0501 1.0000
12.500 0.9635 0.05250 0.04725 0.0513 0.0489 1.0000
12.750 0.9503 0.05514 0.05005 0.0535 0.0483 1.0000
13.000 0.9867 0.05605 0.05070 0.0526 0.0460 1.0000
13.500 0.9393 0.06506 0.06006 0.0551 0.0453 1.0000
13.750 0.9122 0.06960 0.06481 0.0549 0.0453 1.0000
14.000 0.8831 0.07495 0.07032 0.0533 0.0453 1.0000
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