GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 379 AIRFOIL (goe379-il) Reynolds number: 100,000 Max Cl/Cd: 60.29 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe379-il-100000-n5.txt Download as CSV file: xf-goe379-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 379 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2928 0.10363 0.09919 -0.0296 1.0000 0.0290
-7.500 -0.2955 0.10175 0.09740 -0.0291 1.0000 0.0290
-7.250 -0.2990 0.10042 0.09617 -0.0297 1.0000 0.0291
-7.000 -0.3013 0.09861 0.09445 -0.0293 1.0000 0.0291
-6.750 -0.2966 0.09230 0.08819 -0.0237 1.0000 0.0302
-6.500 -0.3026 0.09071 0.08668 -0.0221 1.0000 0.0303
-6.250 -0.2858 0.08682 0.08280 -0.0252 0.9946 0.0316
-6.000 -0.2593 0.08258 0.07854 -0.0315 0.9864 0.0327
-5.750 -0.2313 0.07841 0.07433 -0.0381 0.9780 0.0341
-5.500 -0.2014 0.07440 0.07027 -0.0452 0.9686 0.0359
-5.250 -0.1580 0.07102 0.06675 -0.0568 0.9581 0.0377
-5.000 -0.1179 0.06730 0.06283 -0.0651 0.9496 0.0380
-4.750 -0.0820 0.06319 0.05858 -0.0710 0.9425 0.0381
-4.500 -0.0545 0.05873 0.05405 -0.0744 0.9342 0.0383
-4.250 -0.0191 0.05486 0.04997 -0.0788 0.9275 0.0381
-4.000 -0.0069 0.04948 0.04465 -0.0783 0.9183 0.0280
-3.750 0.0248 0.04577 0.04078 -0.0816 0.9106 0.0271
-3.500 0.0580 0.04228 0.03708 -0.0846 0.9015 0.0274
-3.250 0.0882 0.03901 0.03357 -0.0866 0.8920 0.0268
-3.000 0.1225 0.03555 0.02982 -0.0888 0.8848 0.0259
-2.750 0.1511 0.03255 0.02652 -0.0894 0.8741 0.0253
-2.500 0.1810 0.02947 0.02306 -0.0897 0.8644 0.0253
-2.250 0.2126 0.02638 0.01949 -0.0900 0.8558 0.0259
-2.000 0.2423 0.02327 0.01572 -0.0894 0.8456 0.0287
-1.750 0.2700 0.02131 0.01334 -0.0888 0.8341 0.0308
-1.500 0.2986 0.01971 0.01129 -0.0883 0.8219 0.0347
-1.250 0.3270 0.01867 0.00993 -0.0878 0.8090 0.0435
-1.000 0.3552 0.01766 0.00863 -0.0872 0.7961 0.0563
-0.750 0.3828 0.01710 0.00780 -0.0867 0.7833 0.0740
-0.500 0.4102 0.01654 0.00707 -0.0863 0.7708 0.0864
-0.250 0.4375 0.01597 0.00637 -0.0858 0.7584 0.0937
0.000 0.4639 0.01564 0.00592 -0.0853 0.7451 0.1057
0.250 0.4921 0.01532 0.00546 -0.0851 0.7315 0.1147
0.500 0.5194 0.01508 0.00511 -0.0848 0.7178 0.1262
0.750 0.5462 0.01489 0.00489 -0.0844 0.7040 0.1498
1.000 0.5728 0.01463 0.00470 -0.0841 0.6901 0.2084
1.500 0.6623 0.01319 0.00440 -0.0913 0.6598 1.0000
1.750 0.6869 0.01334 0.00438 -0.0905 0.6452 1.0000
2.000 0.7115 0.01351 0.00440 -0.0898 0.6308 1.0000
2.250 0.7360 0.01369 0.00445 -0.0890 0.6164 1.0000
2.500 0.7603 0.01388 0.00455 -0.0882 0.6020 1.0000
2.750 0.7846 0.01409 0.00466 -0.0874 0.5878 1.0000
3.000 0.8087 0.01431 0.00480 -0.0866 0.5739 1.0000
3.250 0.8328 0.01455 0.00498 -0.0858 0.5604 1.0000
3.500 0.8568 0.01481 0.00522 -0.0851 0.5470 1.0000
3.750 0.8806 0.01508 0.00546 -0.0843 0.5337 1.0000
4.000 0.9043 0.01537 0.00572 -0.0835 0.5205 1.0000
4.250 0.9278 0.01566 0.00601 -0.0827 0.5069 1.0000
4.500 0.9510 0.01597 0.00636 -0.0818 0.4927 1.0000
4.750 0.9738 0.01629 0.00669 -0.0808 0.4778 1.0000
5.000 0.9965 0.01661 0.00704 -0.0799 0.4632 1.0000
5.250 1.0193 0.01695 0.00747 -0.0790 0.4499 1.0000
5.500 1.0423 0.01730 0.00791 -0.0781 0.4387 1.0000
5.750 1.0653 0.01768 0.00838 -0.0773 0.4284 1.0000
6.000 1.0882 0.01805 0.00893 -0.0764 0.4175 1.0000
6.250 1.1066 0.01839 0.00928 -0.0747 0.3906 1.0000
6.500 1.1225 0.01885 0.00970 -0.0726 0.3557 1.0000
6.750 1.1358 0.01952 0.01021 -0.0703 0.3036 1.0000
7.000 1.1449 0.02072 0.01094 -0.0674 0.2109 1.0000
7.250 1.1361 0.02396 0.01288 -0.0629 0.0429 1.0000
7.500 1.1429 0.02576 0.01456 -0.0599 0.0240 1.0000
7.750 1.1545 0.02704 0.01606 -0.0574 0.0207 1.0000
8.000 1.1630 0.02848 0.01774 -0.0547 0.0190 1.0000
8.250 1.1676 0.03008 0.01958 -0.0515 0.0175 1.0000
8.500 1.1719 0.03143 0.02115 -0.0484 0.0164 1.0000
8.750 1.1734 0.03296 0.02290 -0.0451 0.0155 1.0000
9.000 1.1716 0.03480 0.02502 -0.0418 0.0150 1.0000
9.250 1.1694 0.03679 0.02720 -0.0389 0.0146 1.0000
9.500 1.1678 0.03892 0.02948 -0.0365 0.0143 1.0000
9.750 1.1664 0.04121 0.03190 -0.0343 0.0140 1.0000
10.000 1.1679 0.04350 0.03430 -0.0324 0.0138 1.0000
10.250 1.1728 0.04572 0.03661 -0.0306 0.0131 1.0000
10.500 1.1820 0.04782 0.03879 -0.0290 0.0126 1.0000
10.750 1.1925 0.05024 0.04127 -0.0274 0.0115 1.0000
11.000 1.2108 0.05301 0.04413 -0.0260 0.0108 1.0000
11.250 1.2277 0.05601 0.04734 -0.0248 0.0107 1.0000
11.500 1.2376 0.05932 0.05091 -0.0235 0.0106 1.0000
11.750 1.2404 0.06270 0.05456 -0.0223 0.0106 1.0000
12.000 1.2383 0.06625 0.05839 -0.0212 0.0107 1.0000
12.250 1.2336 0.06947 0.06187 -0.0205 0.0108 1.0000
12.500 1.2260 0.07326 0.06593 -0.0200 0.0108 1.0000
12.750 1.2165 0.07730 0.07024 -0.0201 0.0109 1.0000
13.000 1.2051 0.08174 0.07494 -0.0206 0.0109 1.0000
13.250 1.1932 0.08632 0.07975 -0.0216 0.0110 1.0000
13.500 1.1804 0.09122 0.08489 -0.0231 0.0111 1.0000
13.750 1.1655 0.09679 0.09070 -0.0253 0.0112 1.0000
14.000 1.1511 0.10248 0.09660 -0.0280 0.0113 1.0000
14.250 1.1360 0.10874 0.10307 -0.0312 0.0114 1.0000
14.500 1.1215 0.11530 0.10982 -0.0350 0.0116 1.0000
14.750 1.1055 0.12267 0.11738 -0.0394 0.0117 1.0000
15.000 1.0902 0.13043 0.12532 -0.0444 0.0118 1.0000
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Polar data table (+)
Polar graphs
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