GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 517 AIRFOIL (goe517-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.71 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe517-il-1000000.txt Download as CSV file: xf-goe517-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 517 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2806 0.08537 0.08386 -0.0274 1.0000 0.0107
-8.750 -0.2783 0.08235 0.08085 -0.0277 1.0000 0.0111
-8.500 -0.2772 0.07912 0.07763 -0.0281 1.0000 0.0116
-8.250 -0.2775 0.07581 0.07434 -0.0283 1.0000 0.0119
-8.000 -0.2798 0.07234 0.07090 -0.0287 1.0000 0.0126
-7.750 -0.3630 0.08344 0.08193 -0.0246 1.0000 0.0111
-7.500 -0.3715 0.08149 0.08001 -0.0232 1.0000 0.0113
-7.250 -0.3647 0.07788 0.07643 -0.0264 0.9988 0.0117
-7.000 -0.3356 0.07142 0.06993 -0.0379 0.9932 0.0129
-6.750 -0.3068 0.06594 0.06441 -0.0465 0.9867 0.0132
-6.500 -0.2793 0.06024 0.05866 -0.0541 0.9798 0.0132
-6.250 -0.2483 0.05451 0.05285 -0.0617 0.9724 0.0132
-5.750 -0.2187 0.01628 0.01274 -0.0790 0.9309 0.0113
-5.500 -0.1951 0.01440 0.01048 -0.0784 0.9156 0.0116
-5.250 -0.1713 0.01303 0.00877 -0.0776 0.9012 0.0121
-5.000 -0.1466 0.01212 0.00762 -0.0769 0.8881 0.0126
-4.750 -0.1202 0.01188 0.00725 -0.0764 0.8767 0.0131
-4.500 -0.0973 0.01032 0.00537 -0.0755 0.8662 0.0141
-4.250 -0.0715 0.00995 0.00492 -0.0750 0.8565 0.0150
-4.000 -0.0455 0.00957 0.00443 -0.0744 0.8467 0.0157
-3.750 -0.0196 0.00920 0.00395 -0.0739 0.8364 0.0166
-3.500 0.0065 0.00896 0.00361 -0.0733 0.8263 0.0175
-3.250 0.0319 0.00840 0.00294 -0.0726 0.8165 0.0189
-3.000 0.0579 0.00812 0.00260 -0.0721 0.8075 0.0208
-2.750 0.0842 0.00793 0.00234 -0.0716 0.7983 0.0225
-2.500 0.1108 0.00778 0.00214 -0.0712 0.7882 0.0240
-2.250 0.1365 0.00743 0.00173 -0.0706 0.7782 0.0279
-2.000 0.1628 0.00732 0.00157 -0.0701 0.7676 0.0316
-1.750 0.1889 0.00713 0.00136 -0.0696 0.7548 0.0398
-1.500 0.2151 0.00702 0.00125 -0.0691 0.7407 0.0540
-1.250 0.2415 0.00697 0.00118 -0.0687 0.7252 0.0673
-1.000 0.2678 0.00693 0.00113 -0.0683 0.7075 0.0779
-0.750 0.2939 0.00692 0.00106 -0.0678 0.6864 0.0856
-0.500 0.3197 0.00697 0.00102 -0.0673 0.6606 0.0932
-0.250 0.3450 0.00702 0.00097 -0.0666 0.6306 0.1016
0.000 0.3706 0.00710 0.00096 -0.0661 0.6038 0.1100
0.250 0.3963 0.00715 0.00095 -0.0656 0.5825 0.1230
0.500 0.4221 0.00717 0.00095 -0.0651 0.5656 0.1401
1.000 0.4731 0.00697 0.00102 -0.0642 0.5414 0.2796
1.250 0.5278 0.00542 0.00122 -0.0707 0.5301 0.9868
1.500 0.5837 0.00555 0.00125 -0.0770 0.5180 0.9993
2.000 0.6375 0.00572 0.00132 -0.0766 0.5004 1.0000
2.250 0.6622 0.00581 0.00138 -0.0759 0.4914 1.0000
2.500 0.6870 0.00591 0.00143 -0.0752 0.4807 1.0000
2.750 0.7119 0.00599 0.00148 -0.0745 0.4695 1.0000
3.000 0.7367 0.00610 0.00154 -0.0738 0.4566 1.0000
3.250 0.7607 0.00625 0.00162 -0.0730 0.4360 1.0000
3.500 0.7843 0.00645 0.00170 -0.0722 0.4059 1.0000
3.750 0.8072 0.00671 0.00183 -0.0712 0.3745 1.0000
4.250 0.8535 0.00721 0.00214 -0.0694 0.3315 1.0000
4.500 0.8770 0.00743 0.00231 -0.0685 0.3159 1.0000
4.750 0.9004 0.00767 0.00248 -0.0677 0.2985 1.0000
5.000 0.9241 0.00789 0.00264 -0.0669 0.2845 1.0000
5.250 0.9478 0.00811 0.00282 -0.0661 0.2694 1.0000
5.500 0.9717 0.00831 0.00299 -0.0654 0.2570 1.0000
5.750 0.9952 0.00856 0.00318 -0.0646 0.2406 1.0000
6.000 1.0180 0.00885 0.00339 -0.0637 0.2215 1.0000
6.250 1.0410 0.00913 0.00362 -0.0628 0.2018 1.0000
6.500 1.0620 0.00960 0.00393 -0.0617 0.1691 1.0000
6.750 1.0758 0.01069 0.00458 -0.0595 0.0926 1.0000
7.000 1.0930 0.01151 0.00518 -0.0577 0.0545 1.0000
7.250 1.1117 0.01221 0.00572 -0.0562 0.0290 1.0000
7.500 1.1324 0.01271 0.00622 -0.0550 0.0219 1.0000
7.750 1.1533 0.01319 0.00670 -0.0538 0.0186 1.0000
8.000 1.1737 0.01372 0.00729 -0.0525 0.0162 1.0000
8.250 1.1951 0.01412 0.00773 -0.0515 0.0150 1.0000
8.500 1.2156 0.01460 0.00824 -0.0503 0.0137 1.0000
8.750 1.2329 0.01535 0.00907 -0.0486 0.0123 1.0000
9.000 1.2499 0.01608 0.00990 -0.0469 0.0116 1.0000
9.250 1.2696 0.01656 0.01043 -0.0457 0.0110 1.0000
9.500 1.2887 0.01705 0.01096 -0.0444 0.0104 1.0000
9.750 1.3065 0.01762 0.01158 -0.0429 0.0097 1.0000
10.000 1.3226 0.01827 0.01229 -0.0412 0.0092 1.0000
10.250 1.3322 0.01934 0.01344 -0.0384 0.0087 1.0000
10.500 1.3315 0.02077 0.01501 -0.0340 0.0082 1.0000
10.750 1.3428 0.02141 0.01572 -0.0315 0.0080 1.0000
11.000 1.3509 0.02227 0.01667 -0.0287 0.0079 1.0000
11.250 1.3600 0.02312 0.01759 -0.0263 0.0076 1.0000
11.500 1.3665 0.02419 0.01875 -0.0237 0.0074 1.0000
11.750 1.3712 0.02545 0.02010 -0.0211 0.0073 1.0000
12.000 1.3775 0.02666 0.02140 -0.0190 0.0070 1.0000
12.250 1.3835 0.02798 0.02282 -0.0172 0.0068 1.0000
12.500 1.3845 0.02980 0.02475 -0.0151 0.0067 1.0000
12.750 1.3934 0.03102 0.02602 -0.0140 0.0065 1.0000
13.000 1.3979 0.03270 0.02777 -0.0128 0.0063 1.0000
13.250 1.3997 0.03472 0.02987 -0.0118 0.0060 1.0000
13.500 1.3948 0.03756 0.03283 -0.0106 0.0059 1.0000
13.750 1.3793 0.04171 0.03716 -0.0094 0.0057 1.0000
14.000 1.3746 0.04488 0.04046 -0.0089 0.0057 1.0000
14.250 1.3663 0.04867 0.04441 -0.0088 0.0056 1.0000
14.500 1.3620 0.05211 0.04798 -0.0090 0.0055 1.0000
14.750 1.3613 0.05527 0.05126 -0.0097 0.0055 1.0000
15.000 1.3610 0.05852 0.05463 -0.0107 0.0053 1.0000
15.250 1.3527 0.06296 0.05922 -0.0119 0.0053 1.0000
15.500 1.3446 0.06750 0.06388 -0.0133 0.0052 1.0000
15.750 1.3388 0.07193 0.06844 -0.0150 0.0051 1.0000
16.000 1.3238 0.07778 0.07444 -0.0169 0.0051 1.0000
16.250 1.3114 0.08348 0.08029 -0.0192 0.0051 1.0000
16.500 1.3030 0.08886 0.08578 -0.0217 0.0050 1.0000
16.750 1.2890 0.09527 0.09233 -0.0247 0.0050 1.0000
17.000 1.2720 0.10250 0.09971 -0.0281 0.0050 1.0000
17.250 1.2565 0.10979 0.10714 -0.0318 0.0050 1.0000
17.500 1.2377 0.11793 0.11544 -0.0360 0.0050 1.0000
17.750 1.2216 0.12581 0.12344 -0.0403 0.0051 1.0000
18.000 1.2075 0.13353 0.13127 -0.0447 0.0050 1.0000
18.250 1.1905 0.14211 0.13998 -0.0496 0.0050 1.0000
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Polar data table (+)
Polar graphs
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