GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il) Reynolds number: 100,000 Max Cl/Cd: 60.39 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe184-il-100000-n5.txt Download as CSV file: xf-goe184-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3030 0.10140 0.09666 -0.0276 1.0000 0.0582
-8.000 -0.3097 0.09979 0.09517 -0.0298 1.0000 0.0586
-7.750 -0.3137 0.09771 0.09319 -0.0323 1.0000 0.0588
-7.500 -0.3003 0.09316 0.08866 -0.0282 1.0000 0.0597
-7.250 -0.2990 0.09062 0.08619 -0.0276 1.0000 0.0602
-7.000 -0.3004 0.08835 0.08401 -0.0271 1.0000 0.0606
-6.750 -0.3045 0.08631 0.08206 -0.0264 1.0000 0.0608
-6.250 -0.2535 0.07486 0.07048 -0.0434 0.9814 0.0496
-5.750 -0.1811 0.06025 0.05558 -0.0666 0.9622 0.0429
-5.500 -0.1522 0.05662 0.05188 -0.0711 0.9520 0.0442
-5.250 -0.1211 0.05362 0.04879 -0.0753 0.9427 0.0465
-5.000 -0.0824 0.04783 0.04277 -0.0833 0.9334 0.0462
-4.750 -0.0460 0.04235 0.03700 -0.0898 0.9223 0.0463
-4.500 -0.0077 0.03714 0.03139 -0.0956 0.9127 0.0487
-4.250 0.0303 0.03108 0.02472 -0.1007 0.9032 0.0492
-4.000 0.0650 0.02614 0.01902 -0.1038 0.8927 0.0501
-3.750 0.0969 0.02458 0.01716 -0.1050 0.8826 0.0523
-3.500 0.1282 0.02320 0.01548 -0.1058 0.8718 0.0547
-3.250 0.1589 0.02134 0.01315 -0.1064 0.8598 0.0563
-3.000 0.1895 0.01974 0.01108 -0.1067 0.8481 0.0586
-2.750 0.2185 0.01908 0.01031 -0.1067 0.8351 0.0608
-2.500 0.2472 0.01833 0.00932 -0.1064 0.8204 0.0650
-2.250 0.2751 0.01780 0.00860 -0.1059 0.8038 0.0712
-2.000 0.3028 0.01719 0.00776 -0.1054 0.7869 0.0800
-1.750 0.3302 0.01676 0.00718 -0.1049 0.7706 0.0897
-1.500 0.3574 0.01648 0.00685 -0.1045 0.7557 0.0991
-1.250 0.3847 0.01631 0.00656 -0.1041 0.7418 0.1083
-1.000 0.4119 0.01616 0.00630 -0.1036 0.7279 0.1141
-0.750 0.4390 0.01609 0.00614 -0.1032 0.7139 0.1234
-0.500 0.4660 0.01603 0.00599 -0.1028 0.7000 0.1314
-0.250 0.4927 0.01595 0.00585 -0.1024 0.6856 0.1390
0.000 0.5194 0.01590 0.00573 -0.1020 0.6710 0.1477
0.250 0.5459 0.01579 0.00560 -0.1015 0.6567 0.1535
0.500 0.5728 0.01572 0.00547 -0.1011 0.6428 0.1582
0.750 0.5999 0.01568 0.00536 -0.1007 0.6291 0.1649
1.000 0.6269 0.01563 0.00529 -0.1004 0.6156 0.1761
1.250 0.6539 0.01557 0.00526 -0.1001 0.6026 0.2004
1.500 0.6807 0.01543 0.00530 -0.0998 0.5904 0.2832
2.000 0.7302 0.01429 0.00534 -0.0981 0.5678 1.0000
2.250 0.7570 0.01453 0.00542 -0.0977 0.5573 1.0000
2.500 0.7837 0.01479 0.00552 -0.0973 0.5476 1.0000
2.750 0.8102 0.01505 0.00571 -0.0970 0.5365 1.0000
3.000 0.8366 0.01533 0.00589 -0.0966 0.5257 1.0000
3.250 0.8629 0.01564 0.00606 -0.0962 0.5155 1.0000
3.500 0.8890 0.01593 0.00633 -0.0959 0.5039 1.0000
3.750 0.9152 0.01623 0.00659 -0.0955 0.4935 1.0000
4.000 0.9413 0.01655 0.00684 -0.0952 0.4844 1.0000
4.250 0.9674 0.01685 0.00720 -0.0949 0.4747 1.0000
4.500 0.9935 0.01718 0.00750 -0.0945 0.4667 1.0000
4.750 1.0193 0.01750 0.00786 -0.0942 0.4571 1.0000
5.000 1.0450 0.01782 0.00822 -0.0938 0.4480 1.0000
5.250 1.0704 0.01813 0.00854 -0.0934 0.4387 1.0000
5.500 1.0956 0.01845 0.00894 -0.0930 0.4287 1.0000
5.750 1.1208 0.01878 0.00930 -0.0925 0.4200 1.0000
6.000 1.1455 0.01911 0.00971 -0.0920 0.4098 1.0000
6.250 1.1701 0.01945 0.01013 -0.0915 0.3996 1.0000
6.500 1.1944 0.01980 0.01053 -0.0909 0.3903 1.0000
6.750 1.2186 0.02018 0.01104 -0.0903 0.3807 1.0000
7.000 1.2426 0.02059 0.01154 -0.0898 0.3717 1.0000
7.250 1.2661 0.02101 0.01203 -0.0891 0.3629 1.0000
7.500 1.2888 0.02145 0.01259 -0.0883 0.3505 1.0000
7.750 1.3096 0.02190 0.01311 -0.0873 0.3336 1.0000
8.000 1.3292 0.02243 0.01365 -0.0861 0.3142 1.0000
8.250 1.3490 0.02298 0.01431 -0.0850 0.2949 1.0000
8.500 1.3682 0.02358 0.01501 -0.0839 0.2745 1.0000
8.750 1.3859 0.02426 0.01575 -0.0826 0.2462 1.0000
9.000 1.4001 0.02517 0.01660 -0.0809 0.2097 1.0000
9.250 1.4081 0.02661 0.01775 -0.0787 0.1778 1.0000
9.500 1.4158 0.02811 0.01915 -0.0765 0.1582 1.0000
9.750 1.4256 0.02944 0.02055 -0.0744 0.1371 1.0000
10.000 1.4304 0.03100 0.02206 -0.0719 0.1021 1.0000
10.250 1.4242 0.03330 0.02411 -0.0686 0.0770 1.0000
10.500 1.4202 0.03562 0.02636 -0.0658 0.0516 1.0000
10.750 1.4137 0.03831 0.02898 -0.0635 0.0434 1.0000
11.000 1.4082 0.04113 0.03188 -0.0617 0.0397 1.0000
11.500 1.3963 0.04757 0.03858 -0.0596 0.0353 1.0000
11.750 1.3902 0.05110 0.04231 -0.0592 0.0336 1.0000
12.000 1.3825 0.05499 0.04637 -0.0591 0.0321 1.0000
12.250 1.3734 0.05922 0.05076 -0.0593 0.0310 1.0000
12.500 1.3628 0.06381 0.05549 -0.0598 0.0300 1.0000
12.750 1.3514 0.06860 0.06042 -0.0605 0.0293 1.0000
13.000 1.3401 0.07344 0.06539 -0.0612 0.0286 1.0000
13.250 1.3341 0.07759 0.06968 -0.0617 0.0280 1.0000
13.500 1.3295 0.08161 0.07387 -0.0622 0.0274 1.0000
13.750 1.3255 0.08556 0.07798 -0.0626 0.0266 1.0000
14.000 1.3220 0.08947 0.08203 -0.0631 0.0257 1.0000
14.250 1.3188 0.09337 0.08605 -0.0637 0.0248 1.0000
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Polar data table (+)
Polar graphs
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