GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Reynolds number: 50,000 Max Cl/Cd: 28.94 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe314-il-50000.txt Download as CSV file: xf-goe314-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3258 0.11253 0.10536 -0.0200 1.0000 0.1202
-8.750 -0.3304 0.11160 0.10453 -0.0215 1.0000 0.1237
-8.500 -0.3439 0.11203 0.10512 -0.0233 1.0000 0.1248
-8.250 -0.3187 0.10467 0.09774 -0.0212 1.0000 0.1299
-8.000 -0.3156 0.10216 0.09530 -0.0211 1.0000 0.1347
-7.750 -0.3238 0.10119 0.09446 -0.0216 1.0000 0.1383
-7.500 -0.3384 0.10141 0.09484 -0.0241 1.0000 0.1398
-7.250 -0.3233 0.09567 0.08915 -0.0211 1.0000 0.1435
-7.000 -0.3177 0.09272 0.08626 -0.0201 1.0000 0.1490
-6.750 -0.3227 0.09146 0.08511 -0.0218 1.0000 0.1539
-6.500 -0.3281 0.09019 0.08394 -0.0246 1.0000 0.1566
-6.250 -0.3166 0.08549 0.07930 -0.0201 1.0000 0.1624
-6.000 -0.3188 0.08406 0.07795 -0.0213 1.0000 0.1697
-5.750 -0.3190 0.08142 0.07540 -0.0211 1.0000 0.1740
-5.500 -0.3161 0.07884 0.07290 -0.0188 1.0000 0.1826
-5.250 -0.3178 0.07701 0.07111 -0.0198 1.0000 0.1893
-5.000 -0.3158 0.07455 0.06873 -0.0173 1.0000 0.1990
-4.750 -0.3149 0.07217 0.06640 -0.0167 1.0000 0.2068
-4.500 -0.3114 0.07057 0.06477 -0.0181 1.0000 0.2194
-4.250 -0.3088 0.06784 0.06212 -0.0149 1.0000 0.2296
-4.000 -0.3052 0.06540 0.05973 -0.0138 1.0000 0.2419
-3.750 -0.2985 0.06381 0.05809 -0.0147 1.0000 0.2639
-3.500 0.1142 0.03773 0.03150 -0.0282 1.0000 1.0000
-3.250 0.1200 0.03657 0.03047 -0.0278 1.0000 1.0000
-2.250 -0.2993 0.05087 0.04581 0.0062 1.0000 0.4658
-2.000 -0.3001 0.04893 0.04402 0.0112 0.9982 0.5143
-1.750 -0.2734 0.04609 0.04129 0.0131 0.9820 0.5904
-1.500 -0.2435 0.04333 0.03861 0.0137 0.9640 0.6428
-1.250 -0.1978 0.04061 0.03586 0.0091 0.9453 0.6786
-1.000 -0.1210 0.03779 0.03284 -0.0055 0.9254 0.6787
-0.750 0.1121 0.03717 0.02974 -0.0611 0.8985 0.3611
-0.500 0.1937 0.03596 0.02760 -0.0698 0.8808 0.2599
-0.250 0.2606 0.03483 0.02574 -0.0750 0.8641 0.2166
0.000 0.3095 0.03391 0.02437 -0.0775 0.8449 0.2028
0.250 0.3577 0.03240 0.02268 -0.0800 0.8271 0.1936
0.500 0.4024 0.03164 0.02154 -0.0814 0.8094 0.1859
0.750 0.4464 0.03069 0.02037 -0.0827 0.7920 0.1849
1.000 0.4900 0.02984 0.01935 -0.0841 0.7747 0.1905
1.250 0.5277 0.02918 0.01859 -0.0844 0.7576 0.1946
1.500 0.5603 0.02877 0.01807 -0.0839 0.7410 0.2008
1.750 0.5890 0.02840 0.01771 -0.0831 0.7247 0.2161
2.000 0.6161 0.02811 0.01747 -0.0821 0.7089 0.2365
2.250 0.6419 0.02771 0.01740 -0.0811 0.6936 0.2894
2.500 0.6907 0.02637 0.01701 -0.0831 0.6771 1.0000
2.750 0.7154 0.02683 0.01709 -0.0816 0.6618 1.0000
3.000 0.7395 0.02728 0.01730 -0.0802 0.6465 1.0000
3.250 0.7631 0.02778 0.01762 -0.0789 0.6314 1.0000
3.500 0.7866 0.02828 0.01800 -0.0775 0.6163 1.0000
3.750 0.8099 0.02883 0.01843 -0.0762 0.6015 1.0000
4.000 0.8331 0.02941 0.01892 -0.0749 0.5872 1.0000
4.250 0.8568 0.03001 0.01943 -0.0737 0.5733 1.0000
4.500 0.8819 0.03055 0.01989 -0.0726 0.5599 1.0000
4.750 0.9051 0.03127 0.02056 -0.0714 0.5466 1.0000
5.000 0.9235 0.03240 0.02172 -0.0700 0.5328 1.0000
5.250 0.9409 0.03369 0.02309 -0.0687 0.5197 1.0000
5.500 0.9599 0.03495 0.02438 -0.0675 0.5078 1.0000
5.750 0.9883 0.03553 0.02487 -0.0667 0.4976 1.0000
6.000 0.9990 0.03746 0.02697 -0.0652 0.4855 1.0000
6.250 1.0105 0.03947 0.02913 -0.0637 0.4747 1.0000
6.500 1.0407 0.04004 0.02964 -0.0632 0.4665 1.0000
6.750 1.0340 0.04376 0.03365 -0.0613 0.4567 1.0000
7.000 1.0641 0.04453 0.03442 -0.0608 0.4505 1.0000
7.250 1.0324 0.05069 0.04087 -0.0586 0.4424 1.0000
7.500 1.0517 0.05241 0.04266 -0.0578 0.4364 1.0000
7.750 1.0078 0.06009 0.05044 -0.0565 0.4309 1.0000
8.000 0.9112 0.07356 0.06380 -0.0580 0.4299 1.0000
8.250 0.8902 0.08003 0.07027 -0.0595 0.4313 1.0000
8.500 0.8879 0.08504 0.07533 -0.0608 0.4351 1.0000
8.750 0.7302 0.10554 0.09576 -0.0747 0.5804 1.0000
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Polar data table (+)
Polar graphs
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