GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il) Reynolds number: 50,000 Max Cl/Cd: 39.55 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe184-il-50000-n5.txt Download as CSV file: xf-goe184-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 184 (MVA H.29) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2943 0.10049 0.09394 -0.0262 1.0000 0.0978
-7.500 -0.2945 0.09824 0.09179 -0.0263 1.0000 0.0995
-7.250 -0.2960 0.09615 0.08982 -0.0267 1.0000 0.1013
-7.000 -0.2992 0.09443 0.08822 -0.0283 1.0000 0.1032
-6.750 -0.3025 0.09287 0.08678 -0.0309 1.0000 0.1043
-6.500 -0.3037 0.09109 0.08508 -0.0336 1.0000 0.1048
-6.250 -0.3019 0.08738 0.08145 -0.0302 1.0000 0.1064
-6.000 -0.3001 0.08481 0.07895 -0.0266 1.0000 0.1103
-5.750 -0.3009 0.08289 0.07710 -0.0264 1.0000 0.1141
-5.500 -0.2971 0.08164 0.07582 -0.0329 1.0000 0.1189
-5.250 -0.2530 0.07195 0.06583 -0.0453 0.9910 0.0783
-5.000 -0.2274 0.06779 0.06165 -0.0473 0.9832 0.0757
-4.750 -0.1851 0.06259 0.05624 -0.0566 0.9741 0.0765
-4.500 -0.1461 0.05784 0.05128 -0.0638 0.9643 0.0759
-4.250 -0.1065 0.05320 0.04638 -0.0704 0.9548 0.0744
-4.000 -0.0592 0.04833 0.04115 -0.0783 0.9475 0.0748
-3.750 -0.0146 0.04359 0.03587 -0.0852 0.9372 0.0775
-3.500 0.0318 0.03921 0.03091 -0.0912 0.9294 0.0780
-3.250 0.0731 0.03588 0.02711 -0.0954 0.9203 0.0792
-3.000 0.1103 0.03388 0.02485 -0.0981 0.9103 0.0818
-2.750 0.1528 0.03168 0.02218 -0.1014 0.9019 0.0881
-2.500 0.1895 0.02952 0.01948 -0.1034 0.8904 0.0925
-2.250 0.2248 0.02812 0.01784 -0.1049 0.8793 0.0976
-2.000 0.2632 0.02647 0.01573 -0.1065 0.8693 0.1064
-1.750 0.2969 0.02557 0.01463 -0.1072 0.8571 0.1209
-1.500 0.3282 0.02499 0.01393 -0.1075 0.8433 0.1387
-1.250 0.3595 0.02460 0.01337 -0.1077 0.8286 0.1613
-1.000 0.3904 0.02411 0.01271 -0.1077 0.8136 0.1772
-0.750 0.4203 0.02363 0.01210 -0.1073 0.7984 0.1889
-0.500 0.4496 0.02322 0.01148 -0.1068 0.7833 0.1964
-0.250 0.4777 0.02285 0.01102 -0.1062 0.7684 0.2028
0.250 0.5325 0.02236 0.01037 -0.1050 0.7399 0.2220
0.500 0.5595 0.02216 0.01017 -0.1044 0.7263 0.2397
0.750 0.5865 0.02191 0.01005 -0.1039 0.7133 0.2769
1.000 0.6130 0.02123 0.00991 -0.1036 0.7010 0.4142
1.500 0.6627 0.02065 0.00983 -0.1013 0.6736 1.0000
1.750 0.6889 0.02094 0.00994 -0.1008 0.6605 1.0000
2.000 0.7152 0.02123 0.01006 -0.1002 0.6481 1.0000
2.250 0.7418 0.02150 0.01019 -0.0997 0.6365 1.0000
2.500 0.7682 0.02180 0.01036 -0.0992 0.6249 1.0000
2.750 0.7937 0.02216 0.01066 -0.0987 0.6127 1.0000
3.000 0.8196 0.02252 0.01096 -0.0982 0.6014 1.0000
3.250 0.8462 0.02283 0.01118 -0.0977 0.5913 1.0000
3.500 0.8721 0.02323 0.01153 -0.0973 0.5808 1.0000
3.750 0.8976 0.02370 0.01201 -0.0969 0.5705 1.0000
4.000 0.9245 0.02406 0.01230 -0.0964 0.5619 1.0000
4.250 0.9494 0.02461 0.01289 -0.0960 0.5516 1.0000
4.500 0.9749 0.02514 0.01346 -0.0956 0.5425 1.0000
4.750 1.0009 0.02562 0.01395 -0.0951 0.5337 1.0000
5.000 1.0248 0.02626 0.01466 -0.0946 0.5234 1.0000
5.250 1.0506 0.02670 0.01512 -0.0940 0.5141 1.0000
5.500 1.0742 0.02730 0.01581 -0.0933 0.5032 1.0000
5.750 1.0972 0.02793 0.01655 -0.0926 0.4925 1.0000
6.000 1.1224 0.02838 0.01705 -0.0920 0.4830 1.0000
6.250 1.1443 0.02904 0.01787 -0.0911 0.4717 1.0000
6.500 1.1660 0.02969 0.01868 -0.0903 0.4606 1.0000
6.750 1.1897 0.03018 0.01926 -0.0895 0.4508 1.0000
7.000 1.2112 0.03087 0.02017 -0.0886 0.4405 1.0000
7.250 1.2318 0.03165 0.02117 -0.0877 0.4306 1.0000
7.500 1.2555 0.03213 0.02177 -0.0868 0.4214 1.0000
7.750 1.2750 0.03283 0.02270 -0.0857 0.4097 1.0000
8.250 1.3126 0.03415 0.02447 -0.0830 0.3847 1.0000
8.500 1.3313 0.03473 0.02522 -0.0816 0.3716 1.0000
8.750 1.3491 0.03530 0.02595 -0.0800 0.3575 1.0000
9.000 1.3634 0.03589 0.02670 -0.0781 0.3404 1.0000
9.250 1.3748 0.03653 0.02749 -0.0758 0.3212 1.0000
9.500 1.3841 0.03728 0.02833 -0.0734 0.3019 1.0000
9.750 1.3910 0.03834 0.02951 -0.0710 0.2840 1.0000
10.000 1.3931 0.03981 0.03122 -0.0685 0.2652 1.0000
10.250 1.3902 0.04138 0.03292 -0.0656 0.2454 1.0000
10.500 1.3858 0.04332 0.03494 -0.0631 0.2243 1.0000
10.750 1.3819 0.04558 0.03724 -0.0613 0.2056 1.0000
11.250 1.3647 0.05178 0.04323 -0.0588 0.1710 1.0000
11.500 1.3529 0.05580 0.04722 -0.0584 0.1549 1.0000
11.750 1.3418 0.06011 0.05165 -0.0584 0.1396 1.0000
12.000 1.3306 0.06476 0.05648 -0.0589 0.1225 1.0000
12.250 1.3179 0.06975 0.06153 -0.0597 0.1066 1.0000
12.500 1.3040 0.07498 0.06672 -0.0607 0.0949 1.0000
12.750 1.2906 0.08025 0.07194 -0.0617 0.0861 1.0000
13.000 1.2771 0.08557 0.07717 -0.0628 0.0794 1.0000
13.250 1.2678 0.09042 0.08209 -0.0636 0.0723 1.0000
13.500 1.2587 0.09528 0.08696 -0.0645 0.0672 1.0000
13.750 1.2524 0.09981 0.09155 -0.0652 0.0627 1.0000
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Polar data table (+)
Polar graphs
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