GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Reynolds number: 50,000 Max Cl/Cd: 15.19 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe255-il-50000-n5.txt Download as CSV file: xf-goe255-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 255 (MVA CA.6) 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3668 0.11081 0.10449 -0.0596 1.0000 0.0592
-11.750 -0.3973 0.10472 0.09854 -0.0598 1.0000 0.0592
-11.500 -0.4401 0.09668 0.09062 -0.0613 0.9997 0.0585
-11.250 -0.4945 0.08060 0.07432 -0.0731 0.9922 0.0569
-11.000 -0.5206 0.07078 0.06418 -0.0823 0.9827 0.0568
-10.750 -0.5307 0.06415 0.05725 -0.0893 0.9722 0.0576
-10.500 -0.5372 0.05921 0.05201 -0.0941 0.9601 0.0590
-10.250 -0.5401 0.05527 0.04771 -0.0966 0.9474 0.0611
-10.000 -0.5341 0.05221 0.04440 -0.0979 0.9356 0.0640
-9.750 -0.5198 0.05009 0.04223 -0.0991 0.9258 0.0679
-9.500 -0.5051 0.04732 0.03909 -0.1004 0.9172 0.0732
-9.250 -0.4953 0.04556 0.03734 -0.0999 0.9066 0.0783
-9.000 -0.4772 0.04330 0.03481 -0.1010 0.8994 0.0875
-8.750 -0.4650 0.04178 0.03332 -0.1005 0.8899 0.0965
-8.500 -0.4493 0.04025 0.03175 -0.1006 0.8816 0.1089
-8.250 -0.4292 0.03881 0.03019 -0.1012 0.8742 0.1260
-8.000 -0.4123 0.03783 0.02915 -0.1010 0.8657 0.1440
-7.750 -0.3883 0.03694 0.02821 -0.1017 0.8591 0.1650
-7.500 -0.3687 0.03613 0.02727 -0.1014 0.8512 0.1846
-7.250 -0.3437 0.03516 0.02613 -0.1018 0.8447 0.2054
-7.000 -0.3177 0.03447 0.02543 -0.1020 0.8386 0.2240
-6.750 -0.2956 0.03402 0.02497 -0.1014 0.8309 0.2417
-6.500 -0.2632 0.03353 0.02443 -0.1023 0.8265 0.2612
-6.250 -0.2446 0.03350 0.02436 -0.1010 0.8176 0.2770
-6.000 -0.2140 0.03329 0.02403 -0.1014 0.8122 0.2956
-5.750 -0.1892 0.03326 0.02386 -0.1011 0.8053 0.3132
-5.500 -0.1644 0.03323 0.02364 -0.1008 0.7982 0.3320
-5.250 -0.1315 0.03321 0.02349 -0.1014 0.7939 0.3513
-5.000 -0.1147 0.03347 0.02364 -0.0998 0.7850 0.3673
-4.750 -0.0862 0.03336 0.02336 -0.1000 0.7798 0.3847
-4.500 -0.0529 0.03306 0.02287 -0.1009 0.7763 0.4021
-4.250 -0.0399 0.03333 0.02302 -0.0990 0.7667 0.4152
-4.000 -0.0097 0.03310 0.02261 -0.0995 0.7621 0.4310
-3.750 0.0143 0.03312 0.02250 -0.0990 0.7562 0.4449
-3.500 0.0336 0.03332 0.02265 -0.0979 0.7489 0.4563
-3.250 0.0641 0.03315 0.02235 -0.0983 0.7450 0.4703
-3.000 0.0847 0.03338 0.02243 -0.0977 0.7389 0.4828
-2.750 0.1027 0.03374 0.02275 -0.0965 0.7324 0.4936
-2.500 0.1311 0.03373 0.02264 -0.0967 0.7287 0.5059
-2.250 0.1636 0.03359 0.02235 -0.0975 0.7261 0.5189
-2.000 0.1672 0.03460 0.02337 -0.0946 0.7168 0.5275
-1.750 0.1941 0.03470 0.02339 -0.0947 0.7128 0.5393
-1.500 0.2256 0.03466 0.02323 -0.0954 0.7100 0.5528
-1.250 0.2289 0.03586 0.02445 -0.0927 0.7020 0.5624
-1.000 0.2501 0.03632 0.02488 -0.0921 0.6978 0.5748
-0.750 0.2776 0.03652 0.02502 -0.0924 0.6950 0.5884
-0.250 0.3001 0.03843 0.02694 -0.0893 0.6834 0.6085
0.000 0.3256 0.03877 0.02723 -0.0894 0.6799 0.6203
0.250 0.3560 0.03889 0.02732 -0.0900 0.6776 0.6325
0.750 0.3711 0.04136 0.02987 -0.0865 0.6648 0.6553
1.000 0.4045 0.04106 0.02959 -0.0870 0.6617 0.6727
1.500 0.4312 0.04266 0.03137 -0.0841 0.6479 0.7121
1.750 0.4667 0.04182 0.03065 -0.0841 0.6450 0.7493
2.250 0.5035 0.04240 0.03161 -0.0817 0.6300 1.0000
2.500 0.5081 0.04405 0.03315 -0.0803 0.6195 1.0000
2.750 0.5421 0.04394 0.03286 -0.0812 0.6153 1.0000
3.000 0.5784 0.04365 0.03242 -0.0822 0.6124 1.0000
3.250 0.5731 0.04612 0.03486 -0.0800 0.6013 1.0000
3.500 0.6087 0.04580 0.03443 -0.0807 0.5982 1.0000
3.750 0.6069 0.04803 0.03664 -0.0787 0.5872 1.0000
4.000 0.6399 0.04781 0.03635 -0.0791 0.5834 1.0000
4.500 0.6728 0.04968 0.03816 -0.0776 0.5683 1.0000
4.750 0.7083 0.04914 0.03757 -0.0779 0.5653 1.0000
5.000 0.7074 0.05133 0.03978 -0.0761 0.5527 1.0000
5.250 0.7371 0.05116 0.03958 -0.0759 0.5481 1.0000
5.500 0.7427 0.05287 0.04131 -0.0745 0.5365 1.0000
5.750 0.7782 0.05215 0.04057 -0.0746 0.5336 1.0000
6.000 0.7764 0.05458 0.04304 -0.0729 0.5199 1.0000
6.250 0.8111 0.05385 0.04231 -0.0729 0.5170 1.0000
6.500 0.8089 0.05639 0.04489 -0.0712 0.5029 1.0000
6.750 0.8436 0.05555 0.04405 -0.0711 0.5001 1.0000
7.000 0.8391 0.05841 0.04695 -0.0696 0.4857 1.0000
7.250 0.8732 0.05761 0.04617 -0.0693 0.4831 1.0000
7.750 0.8568 0.06476 0.05341 -0.0668 0.4553 1.0000
8.000 0.8860 0.06438 0.05306 -0.0664 0.4521 1.0000
8.250 0.8754 0.06848 0.05721 -0.0655 0.4389 1.0000
8.500 0.9038 0.06820 0.05698 -0.0651 0.4362 1.0000
8.750 0.8888 0.07309 0.06192 -0.0644 0.4236 1.0000
9.000 0.9173 0.07271 0.06160 -0.0640 0.4210 1.0000
9.250 0.9027 0.07757 0.06651 -0.0634 0.4088 1.0000
9.500 0.9316 0.07694 0.06594 -0.0628 0.4056 1.0000
9.750 0.9217 0.08112 0.07019 -0.0624 0.3940 1.0000
10.250 0.9421 0.08442 0.07361 -0.0613 0.3795 1.0000
10.500 0.9742 0.08310 0.07237 -0.0605 0.3769 1.0000
11.000 0.9859 0.08782 0.07725 -0.0597 0.3626 1.0000
11.500 0.9936 0.09327 0.08287 -0.0592 0.3482 1.0000
12.000 0.9998 0.09903 0.08880 -0.0589 0.3333 1.0000
12.250 1.0307 0.09762 0.08751 -0.0579 0.3310 1.0000
12.750 1.0291 0.10471 0.09479 -0.0580 0.3153 1.0000
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Polar data table (+)
Polar graphs
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