GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Reynolds number: 200,000 Max Cl/Cd: 76.21 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe116-il-200000-n5.txt Download as CSV file: xf-goe116-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 116 (MVA MK.3) 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2793 0.09889 0.09579 -0.0380 1.0000 0.0132
-10.000 -0.2799 0.09473 0.09165 -0.0389 1.0000 0.0126
-9.500 -0.3835 0.10164 0.09834 -0.0307 1.0000 0.0133
-9.250 -0.3826 0.09747 0.09422 -0.0324 1.0000 0.0124
-9.000 -0.3812 0.09326 0.09005 -0.0343 1.0000 0.0118
-8.750 -0.3805 0.08892 0.08577 -0.0363 1.0000 0.0113
-8.500 -0.3813 0.08441 0.08133 -0.0386 1.0000 0.0108
-8.250 -0.3835 0.07955 0.07654 -0.0413 0.9937 0.0104
-8.000 -0.3804 0.07194 0.06895 -0.0487 0.9541 0.0097
-7.750 -0.3849 0.05449 0.05131 -0.0700 0.9164 0.0086
-7.500 -0.3645 0.04241 0.03858 -0.0863 0.8923 0.0083
-7.250 -0.3468 0.03759 0.03321 -0.0907 0.8742 0.0082
-7.000 -0.3283 0.03366 0.02874 -0.0929 0.8596 0.0082
-6.750 -0.3110 0.02930 0.02393 -0.0944 0.8474 0.0087
-6.500 -0.2895 0.02685 0.02119 -0.0951 0.8367 0.0096
-6.250 -0.2658 0.02480 0.01876 -0.0954 0.8269 0.0103
-6.000 -0.2408 0.02276 0.01630 -0.0955 0.8177 0.0104
-5.750 -0.2151 0.02104 0.01424 -0.0954 0.8093 0.0104
-5.500 -0.1890 0.01961 0.01248 -0.0953 0.8018 0.0105
-5.250 -0.1624 0.01838 0.01105 -0.0952 0.7944 0.0108
-5.000 -0.1357 0.01739 0.00987 -0.0951 0.7876 0.0112
-4.750 -0.1083 0.01659 0.00892 -0.0951 0.7806 0.0118
-4.500 -0.0807 0.01604 0.00816 -0.0952 0.7742 0.0135
-4.250 -0.0525 0.01550 0.00741 -0.0953 0.7681 0.0143
-4.000 -0.0241 0.01476 0.00628 -0.0953 0.7622 0.0156
-3.750 0.0041 0.01418 0.00541 -0.0953 0.7569 0.0184
-3.500 0.0324 0.01364 0.00473 -0.0954 0.7508 0.0242
-3.250 0.0599 0.01308 0.00452 -0.0956 0.7457 0.1284
-3.000 0.0886 0.01337 0.00462 -0.0957 0.7404 0.1447
-2.750 0.1171 0.01366 0.00483 -0.0958 0.7349 0.1566
-2.500 0.1450 0.01390 0.00499 -0.0959 0.7303 0.1682
-2.250 0.1733 0.01385 0.00481 -0.0961 0.7250 0.1722
-2.000 0.2013 0.01369 0.00455 -0.0962 0.7200 0.1733
-1.750 0.2293 0.01356 0.00431 -0.0963 0.7157 0.1744
-1.500 0.2574 0.01340 0.00410 -0.0964 0.7106 0.1755
-1.250 0.2852 0.01322 0.00391 -0.0965 0.7057 0.1769
-1.000 0.3130 0.01310 0.00376 -0.0966 0.7016 0.1783
-0.750 0.3411 0.01300 0.00367 -0.0968 0.6966 0.1803
-0.500 0.3690 0.01291 0.00359 -0.0969 0.6918 0.1825
-0.250 0.3969 0.01286 0.00350 -0.0970 0.6877 0.1846
0.000 0.4250 0.01279 0.00345 -0.0972 0.6830 0.1864
0.250 0.4530 0.01275 0.00342 -0.0973 0.6783 0.1883
0.500 0.4809 0.01270 0.00338 -0.0974 0.6743 0.1901
0.750 0.5088 0.01264 0.00340 -0.0976 0.6701 0.1925
1.000 0.5368 0.01261 0.00344 -0.0977 0.6653 0.1952
1.250 0.5647 0.01260 0.00347 -0.0978 0.6612 0.1984
1.500 0.5927 0.01262 0.00353 -0.0980 0.6575 0.2021
1.750 0.6206 0.01261 0.00364 -0.0981 0.6526 0.2062
2.000 0.6485 0.01262 0.00374 -0.0983 0.6483 0.2118
2.250 0.6765 0.01265 0.00385 -0.0984 0.6447 0.2193
2.500 0.7042 0.01265 0.00402 -0.0985 0.6394 0.2321
2.750 0.7318 0.01259 0.00416 -0.0986 0.6333 0.2632
3.250 0.7827 0.01115 0.00451 -0.0976 0.6201 1.0000
3.500 0.8098 0.01124 0.00465 -0.0974 0.6109 1.0000
3.750 0.8346 0.01118 0.00453 -0.0965 0.5785 1.0000
4.000 0.8589 0.01127 0.00454 -0.0957 0.5347 1.0000
4.250 0.8745 0.01216 0.00470 -0.0935 0.3956 1.0000
4.750 0.8865 0.01698 0.00755 -0.0879 0.0200 1.0000
5.000 0.9068 0.01783 0.00856 -0.0866 0.0166 1.0000
5.250 0.9283 0.01848 0.00935 -0.0857 0.0145 1.0000
5.500 0.9476 0.01934 0.01039 -0.0843 0.0130 1.0000
5.750 0.9643 0.02039 0.01157 -0.0826 0.0121 1.0000
6.000 0.9785 0.02159 0.01287 -0.0806 0.0115 1.0000
6.250 0.9911 0.02289 0.01423 -0.0784 0.0108 1.0000
6.500 1.0009 0.02448 0.01585 -0.0759 0.0096 1.0000
6.750 1.0106 0.02670 0.01808 -0.0733 0.0087 1.0000
7.000 1.0298 0.02808 0.01953 -0.0719 0.0085 1.0000
7.250 1.0519 0.02968 0.02123 -0.0708 0.0083 1.0000
7.500 1.0766 0.03154 0.02322 -0.0701 0.0081 1.0000
7.750 1.1023 0.03371 0.02556 -0.0695 0.0080 1.0000
8.000 1.1267 0.03618 0.02832 -0.0687 0.0080 1.0000
8.250 1.1483 0.03897 0.03139 -0.0676 0.0080 1.0000
8.500 1.1656 0.04135 0.03406 -0.0660 0.0078 1.0000
8.750 1.1802 0.04343 0.03643 -0.0642 0.0073 1.0000
9.000 1.1918 0.04550 0.03875 -0.0622 0.0066 1.0000
9.250 1.2001 0.04810 0.04163 -0.0599 0.0064 1.0000
9.500 1.2042 0.05140 0.04527 -0.0572 0.0065 1.0000
9.750 1.2024 0.05470 0.04888 -0.0539 0.0066 1.0000
10.000 1.1954 0.05791 0.05237 -0.0503 0.0067 1.0000
10.250 1.1855 0.06126 0.05598 -0.0471 0.0069 1.0000
10.500 1.1731 0.06480 0.05976 -0.0445 0.0070 1.0000
10.750 1.1590 0.06856 0.06375 -0.0425 0.0072 1.0000
11.000 1.1435 0.07264 0.06804 -0.0412 0.0073 1.0000
11.250 1.1269 0.07703 0.07263 -0.0406 0.0074 1.0000
11.500 1.1092 0.08181 0.07760 -0.0406 0.0075 1.0000
11.750 1.0913 0.08694 0.08290 -0.0414 0.0076 1.0000
12.000 1.0727 0.09249 0.08861 -0.0428 0.0076 1.0000
12.250 1.0541 0.09847 0.09475 -0.0450 0.0077 1.0000
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Polar data table (+)
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