GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 379 AIRFOIL (goe379-il) Reynolds number: 200,000 Max Cl/Cd: 77.67 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe379-il-200000.txt Download as CSV file: xf-goe379-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3109 0.09130 0.08828 -0.0291 1.0000 0.0261
-6.500 -0.3148 0.08960 0.08663 -0.0279 1.0000 0.0261
-6.250 -0.3255 0.08568 0.08280 -0.0252 1.0000 0.0264
-6.000 -0.3244 0.08119 0.07835 -0.0224 0.9988 0.0271
-5.750 -0.2993 0.07650 0.07364 -0.0260 0.9945 0.0281
-5.500 -0.2691 0.07218 0.06929 -0.0320 0.9883 0.0294
-5.250 -0.2326 0.06770 0.06474 -0.0397 0.9832 0.0311
-5.000 -0.1976 0.06352 0.06048 -0.0467 0.9755 0.0332
-4.750 -0.1331 0.06014 0.05684 -0.0602 0.9699 0.0365
-4.500 -0.0495 0.03427 0.03110 -0.0712 0.9483 0.0383
-4.250 -0.0228 0.03011 0.02690 -0.0737 0.9432 0.0403
-4.000 0.0049 0.02672 0.02341 -0.0765 0.9344 0.0432
-3.750 0.0577 0.02486 0.02104 -0.0823 0.9277 0.0494
-3.500 0.0689 0.01969 0.01594 -0.0826 0.9167 0.0516
-3.250 0.0907 0.01719 0.01334 -0.0827 0.9049 0.0543
-3.000 0.1158 0.01503 0.01096 -0.0829 0.8929 0.0585
-2.750 0.1465 0.01302 0.00841 -0.0830 0.8818 0.0638
-2.500 0.1664 0.01076 0.00611 -0.0826 0.8718 0.0659
-2.250 0.1885 0.00935 0.00453 -0.0818 0.8597 0.0698
-2.000 0.2247 0.02411 0.01846 -0.0856 0.8757 0.0778
-1.750 0.2523 0.01948 0.01321 -0.0835 0.8648 0.0484
-1.500 0.2784 0.01714 0.01042 -0.0823 0.8533 0.0478
-1.250 0.3053 0.01529 0.00810 -0.0812 0.8416 0.0508
-1.000 0.3314 0.01485 0.00750 -0.0805 0.8286 0.0616
-0.750 0.3577 0.01382 0.00630 -0.0796 0.8157 0.0715
-0.500 0.3834 0.01338 0.00572 -0.0788 0.8017 0.0857
-0.250 0.4089 0.01291 0.00516 -0.0781 0.7875 0.0975
0.000 0.4346 0.01255 0.00465 -0.0772 0.7731 0.1046
0.250 0.4593 0.01214 0.00424 -0.0763 0.7581 0.1151
0.500 0.4837 0.01180 0.00389 -0.0754 0.7427 0.1254
0.750 0.5080 0.01153 0.00361 -0.0744 0.7271 0.1395
1.000 0.5322 0.01130 0.00342 -0.0735 0.7118 0.1680
1.250 0.6199 0.00942 0.00311 -0.0868 0.6933 1.0000
1.500 0.6443 0.00955 0.00307 -0.0859 0.6769 1.0000
1.750 0.6685 0.00969 0.00308 -0.0850 0.6595 1.0000
2.000 0.6927 0.00984 0.00312 -0.0841 0.6428 1.0000
2.250 0.7169 0.01001 0.00316 -0.0832 0.6265 1.0000
2.500 0.7409 0.01020 0.00322 -0.0823 0.6097 1.0000
2.750 0.7647 0.01040 0.00330 -0.0814 0.5919 1.0000
3.000 0.7883 0.01060 0.00342 -0.0805 0.5740 1.0000
3.250 0.8119 0.01083 0.00358 -0.0796 0.5570 1.0000
3.500 0.8355 0.01109 0.00373 -0.0787 0.5406 1.0000
3.750 0.8590 0.01136 0.00391 -0.0778 0.5249 1.0000
4.000 0.8826 0.01161 0.00412 -0.0770 0.5095 1.0000
4.250 0.9062 0.01189 0.00436 -0.0761 0.4956 1.0000
4.500 0.9299 0.01218 0.00466 -0.0753 0.4826 1.0000
4.750 0.9536 0.01246 0.00494 -0.0746 0.4699 1.0000
5.000 0.9771 0.01273 0.00523 -0.0737 0.4573 1.0000
5.250 1.0006 0.01301 0.00556 -0.0729 0.4453 1.0000
5.500 1.0226 0.01326 0.00577 -0.0718 0.4287 1.0000
5.750 1.0440 0.01345 0.00604 -0.0706 0.4082 1.0000
6.000 1.0648 0.01371 0.00627 -0.0693 0.3877 1.0000
6.250 1.0851 0.01398 0.00655 -0.0679 0.3625 1.0000
6.500 1.1042 0.01434 0.00686 -0.0664 0.3327 1.0000
6.750 1.1208 0.01488 0.00725 -0.0644 0.2784 1.0000
7.000 1.1234 0.01686 0.00825 -0.0608 0.1315 1.0000
7.250 1.1240 0.01927 0.01001 -0.0568 0.0343 1.0000
7.500 1.1401 0.02020 0.01111 -0.0547 0.0299 1.0000
7.750 1.1543 0.02123 0.01234 -0.0524 0.0276 1.0000
8.000 1.1639 0.02253 0.01382 -0.0495 0.0259 1.0000
8.250 1.1662 0.02422 0.01566 -0.0458 0.0242 1.0000
8.500 1.1714 0.02560 0.01715 -0.0425 0.0230 1.0000
8.750 1.1749 0.02698 0.01863 -0.0388 0.0224 1.0000
9.000 1.1789 0.02850 0.02024 -0.0354 0.0221 1.0000
9.250 1.1855 0.03024 0.02205 -0.0325 0.0218 1.0000
9.500 1.1975 0.03211 0.02404 -0.0304 0.0218 1.0000
9.750 1.2189 0.03447 0.02649 -0.0293 0.0221 1.0000
10.000 1.2768 0.04059 0.03274 -0.0337 0.0239 1.0000
10.250 1.2959 0.04352 0.03591 -0.0326 0.0240 1.0000
10.500 1.3101 0.04610 0.03873 -0.0308 0.0242 1.0000
16.250 0.8145 0.17673 0.17369 -0.0559 0.0671 1.0000
16.500 0.7915 0.18237 0.17929 -0.0629 0.0656 1.0000
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Polar data table (+)
Polar graphs
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