GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.5 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe335-il-1000000.txt Download as CSV file: xf-goe335-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 335 (D.F.W.) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3340 0.09133 0.08981 -0.0224 1.0000 0.0104
-7.750 -0.3378 0.08896 0.08747 -0.0217 1.0000 0.0104
-7.500 -0.3442 0.08679 0.08534 -0.0206 0.9998 0.0104
-7.250 -0.3264 0.08050 0.07906 -0.0274 0.9969 0.0108
-7.000 -0.3023 0.07701 0.07556 -0.0328 0.9938 0.0111
-6.750 -0.2787 0.07343 0.07197 -0.0384 0.9893 0.0116
-6.500 -0.2497 0.06904 0.06756 -0.0461 0.9846 0.0123
-6.250 -0.2150 0.06370 0.06218 -0.0566 0.9763 0.0141
-5.000 -0.0662 0.01326 0.00918 -0.0947 0.8507 0.0149
-4.750 -0.0397 0.01407 0.00998 -0.0943 0.8293 0.0155
-4.500 -0.0124 0.01511 0.01106 -0.0940 0.8147 0.0160
-4.250 0.0136 0.01499 0.01085 -0.0936 0.8026 0.0169
-4.000 0.0385 0.01337 0.00887 -0.0930 0.7921 0.0186
-3.750 0.0654 0.01331 0.00868 -0.0927 0.7822 0.0195
-3.500 0.0897 0.01173 0.00681 -0.0922 0.7731 0.0213
-3.250 0.1168 0.01187 0.00696 -0.0921 0.7637 0.0224
-3.000 0.1434 0.01153 0.00651 -0.0918 0.7548 0.0238
-2.750 0.1701 0.01109 0.00594 -0.0914 0.7456 0.0252
-2.500 0.1973 0.01097 0.00574 -0.0911 0.7363 0.0263
-2.250 0.2233 0.01001 0.00456 -0.0907 0.7269 0.0280
-2.000 0.2494 0.00922 0.00366 -0.0903 0.7165 0.0291
-1.750 0.2760 0.00885 0.00323 -0.0899 0.7048 0.0304
-1.500 0.3027 0.00866 0.00297 -0.0896 0.6919 0.0320
-1.250 0.3292 0.00840 0.00263 -0.0892 0.6779 0.0330
-1.000 0.3556 0.00815 0.00231 -0.0887 0.6634 0.0337
-0.750 0.3818 0.00795 0.00202 -0.0883 0.6475 0.0342
-0.500 0.4080 0.00779 0.00177 -0.0878 0.6299 0.0347
-0.250 0.4342 0.00768 0.00157 -0.0874 0.6094 0.0354
0.000 0.4602 0.00766 0.00144 -0.0869 0.5844 0.0364
0.250 0.4859 0.00769 0.00132 -0.0864 0.5507 0.0370
0.500 0.5106 0.00778 0.00119 -0.0857 0.5036 0.0387
0.750 0.5352 0.00795 0.00114 -0.0851 0.4577 0.0418
1.000 0.5608 0.00809 0.00115 -0.0846 0.4292 0.0450
1.250 0.5870 0.00817 0.00116 -0.0842 0.4112 0.0502
1.500 0.6126 0.00800 0.00126 -0.0839 0.3990 0.1781
1.750 0.6494 0.00640 0.00150 -0.0866 0.3880 1.0000
2.000 0.6755 0.00651 0.00155 -0.0861 0.3799 1.0000
2.250 0.7013 0.00664 0.00161 -0.0857 0.3718 1.0000
2.500 0.7273 0.00676 0.00169 -0.0853 0.3631 1.0000
2.750 0.7534 0.00688 0.00176 -0.0849 0.3558 1.0000
3.000 0.7795 0.00700 0.00184 -0.0845 0.3497 1.0000
3.250 0.8055 0.00713 0.00194 -0.0841 0.3440 1.0000
3.500 0.8319 0.00724 0.00203 -0.0838 0.3374 1.0000
3.750 0.8577 0.00739 0.00214 -0.0834 0.3313 1.0000
4.000 0.8842 0.00748 0.00224 -0.0831 0.3262 1.0000
4.500 0.9363 0.00775 0.00247 -0.0824 0.3093 1.0000
4.750 0.9620 0.00791 0.00260 -0.0820 0.3013 1.0000
5.000 0.9882 0.00804 0.00272 -0.0817 0.2936 1.0000
5.250 1.0139 0.00821 0.00286 -0.0813 0.2818 1.0000
5.500 1.0389 0.00844 0.00303 -0.0809 0.2628 1.0000
5.750 1.0627 0.00879 0.00323 -0.0803 0.2321 1.0000
6.000 1.0801 0.00981 0.00380 -0.0787 0.1538 1.0000
6.250 1.0943 0.01124 0.00470 -0.0767 0.0566 1.0000
6.500 1.1132 0.01219 0.00541 -0.0752 0.0159 1.0000
6.750 1.1371 0.01254 0.00583 -0.0745 0.0146 1.0000
7.000 1.1601 0.01298 0.00632 -0.0737 0.0131 1.0000
7.250 1.1819 0.01356 0.00697 -0.0727 0.0116 1.0000
7.500 1.2023 0.01427 0.00778 -0.0715 0.0105 1.0000
7.750 1.2248 0.01470 0.00825 -0.0706 0.0099 1.0000
8.000 1.2460 0.01526 0.00888 -0.0696 0.0093 1.0000
8.250 1.2662 0.01588 0.00957 -0.0684 0.0088 1.0000
8.500 1.2856 0.01654 0.01029 -0.0671 0.0084 1.0000
8.750 1.3036 0.01728 0.01109 -0.0656 0.0079 1.0000
9.000 1.3181 0.01829 0.01218 -0.0636 0.0075 1.0000
9.250 1.3160 0.02054 0.01460 -0.0591 0.0070 1.0000
9.500 1.3309 0.02134 0.01549 -0.0572 0.0069 1.0000
9.750 1.3494 0.02180 0.01600 -0.0559 0.0066 1.0000
10.000 1.3596 0.02266 0.01694 -0.0532 0.0064 1.0000
10.250 1.3677 0.02356 0.01791 -0.0503 0.0062 1.0000
10.500 1.3742 0.02460 0.01903 -0.0474 0.0060 1.0000
10.750 1.3780 0.02593 0.02045 -0.0442 0.0058 1.0000
11.000 1.3839 0.02714 0.02175 -0.0417 0.0057 1.0000
11.250 1.3866 0.02876 0.02347 -0.0390 0.0056 1.0000
11.500 1.3921 0.03014 0.02494 -0.0370 0.0054 1.0000
11.750 1.3938 0.03211 0.02701 -0.0348 0.0054 1.0000
12.000 1.3982 0.03373 0.02873 -0.0333 0.0052 1.0000
12.250 1.4007 0.03577 0.03086 -0.0318 0.0052 1.0000
12.500 1.4021 0.03799 0.03319 -0.0306 0.0050 1.0000
12.750 1.4045 0.04005 0.03532 -0.0298 0.0049 1.0000
13.000 1.4035 0.04283 0.03822 -0.0289 0.0049 1.0000
13.250 1.4017 0.04577 0.04128 -0.0282 0.0048 1.0000
13.500 1.3951 0.04957 0.04520 -0.0275 0.0046 1.0000
13.750 1.3883 0.05354 0.04934 -0.0272 0.0046 1.0000
14.000 1.3641 0.06048 0.05660 -0.0273 0.0044 1.0000
14.500 1.3500 0.06857 0.06498 -0.0300 0.0043 1.0000
15.000 1.3223 0.08029 0.07704 -0.0343 0.0044 1.0000
15.250 1.3120 0.08598 0.08288 -0.0373 0.0043 1.0000
15.500 1.2971 0.09282 0.08988 -0.0407 0.0043 1.0000
15.750 1.2873 0.09906 0.09626 -0.0443 0.0042 1.0000
16.250 1.2497 0.11576 0.11328 -0.0535 0.0043 1.0000
16.500 1.2346 0.12386 0.12152 -0.0584 0.0043 1.0000
16.750 1.0669 0.13287 0.13088 -0.0650 0.0046 1.0000
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Polar data table (+)
Polar graphs
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