GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 780 AIRFOIL (goe780-il) Reynolds number: 500,000 Max Cl/Cd: 42.79 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe780-il-500000.txt Download as CSV file: xf-goe780-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 780 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4201 0.05814 0.05611 -0.0747 0.9638 0.0148
-9.500 -0.4341 0.05111 0.04893 -0.0800 0.9506 0.0145
-9.250 -0.4424 0.04603 0.04366 -0.0823 0.9299 0.0149
-9.000 -0.4571 0.04255 0.03997 -0.0801 0.9050 0.0150
-8.750 -0.4735 0.03997 0.03719 -0.0756 0.8882 0.0149
-8.500 -0.4873 0.03758 0.03463 -0.0706 0.8771 0.0152
-8.250 -0.4954 0.03482 0.03170 -0.0665 0.8694 0.0158
-8.000 -0.4961 0.03226 0.02889 -0.0626 0.8630 0.0180
-7.750 -0.4827 0.03212 0.02847 -0.0592 0.8576 0.0194
-7.500 -0.4847 0.02980 0.02590 -0.0548 0.8522 0.0196
-7.250 -0.4838 0.02727 0.02311 -0.0510 0.8479 0.0196
-6.250 -0.4739 0.02068 0.01446 -0.0379 0.8405 0.0129
-6.000 -0.4435 0.01817 0.01161 -0.0384 0.8378 0.0128
-5.750 -0.4124 0.01636 0.00962 -0.0394 0.8353 0.0141
-5.500 -0.3828 0.01522 0.00834 -0.0400 0.8327 0.0150
-5.250 -0.3573 0.01441 0.00746 -0.0398 0.8298 0.0165
-5.000 -0.3336 0.01411 0.00710 -0.0391 0.8269 0.0190
-4.750 -0.3115 0.01310 0.00598 -0.0382 0.8242 0.0203
-4.500 -0.2934 0.01232 0.00515 -0.0364 0.8214 0.0245
-4.250 -0.2709 0.01213 0.00487 -0.0355 0.8189 0.0292
-4.000 -0.2533 0.01157 0.00431 -0.0336 0.8160 0.0389
-3.750 -0.2333 0.01122 0.00389 -0.0322 0.8132 0.0469
-3.500 -0.2121 0.01094 0.00356 -0.0311 0.8106 0.0548
-3.000 -0.1785 0.00984 0.00302 -0.0273 0.8057 0.2190
-2.750 -0.1792 0.00869 0.00276 -0.0219 0.8026 0.4463
-2.500 -0.1957 0.00770 0.00264 -0.0124 0.7991 0.6597
-2.250 -0.1733 0.00723 0.00285 -0.0109 0.7969 0.8202
-2.000 -0.1495 0.00741 0.00304 -0.0098 0.7947 0.8591
-1.750 -0.1241 0.00762 0.00320 -0.0091 0.7927 0.8784
-1.500 -0.0874 0.00795 0.00348 -0.0110 0.7910 0.8930
-1.250 -0.0548 0.00819 0.00370 -0.0120 0.7890 0.9017
-1.000 0.0011 0.00863 0.00411 -0.0182 0.7875 0.9065
-0.750 0.0560 0.00912 0.00456 -0.0241 0.7859 0.9086
-0.500 0.1030 0.00957 0.00498 -0.0283 0.7843 0.9114
-0.250 0.1292 0.00974 0.00513 -0.0280 0.7817 0.9182
0.000 0.1667 0.00986 0.00519 -0.0303 0.7779 0.9190
0.250 0.2026 0.00998 0.00533 -0.0323 0.7750 0.9203
0.500 0.2373 0.01004 0.00541 -0.0340 0.7706 0.9218
0.750 0.2705 0.01007 0.00540 -0.0354 0.7659 0.9237
1.000 0.2885 0.01015 0.00551 -0.0334 0.7627 0.9310
1.250 0.3290 0.01022 0.00564 -0.0363 0.7565 0.9324
1.500 0.3687 0.01011 0.00547 -0.0385 0.7386 0.9342
1.750 0.3967 0.00995 0.00531 -0.0386 0.7173 0.9365
2.000 0.4194 0.00987 0.00521 -0.0374 0.6896 0.9405
2.250 0.4300 0.01005 0.00507 -0.0336 0.5976 0.9453
2.500 0.4157 0.01294 0.00600 -0.0263 0.1151 0.9501
2.750 0.4277 0.01359 0.00632 -0.0234 0.0305 0.9549
3.000 0.4472 0.01389 0.00666 -0.0218 0.0222 0.9581
3.250 0.4765 0.01426 0.00713 -0.0225 0.0200 0.9594
3.500 0.5025 0.01474 0.00770 -0.0224 0.0191 0.9612
3.750 0.5238 0.01532 0.00835 -0.0215 0.0163 0.9636
4.000 0.5369 0.01601 0.00911 -0.0188 0.0156 0.9674
4.250 0.5480 0.01678 0.00995 -0.0156 0.0153 0.9711
4.500 0.5706 0.01806 0.01131 -0.0149 0.0148 0.9724
4.750 0.5984 0.01894 0.01227 -0.0150 0.0157 0.9734
6.750 0.7855 0.04128 0.03657 -0.0093 0.0138 0.9851
7.000 0.8022 0.04390 0.03952 -0.0075 0.0136 0.9871
7.250 0.8278 0.04474 0.04057 -0.0065 0.0126 0.9888
7.500 0.8437 0.04720 0.04326 -0.0044 0.0114 0.9909
7.750 0.8516 0.05016 0.04644 -0.0017 0.0108 0.9933
8.000 0.8589 0.05333 0.04983 0.0005 0.0105 0.9952
8.250 0.8662 0.05690 0.05365 0.0019 0.0101 0.9974
8.500 0.8711 0.06057 0.05751 0.0033 0.0098 0.9996
8.750 0.8618 0.06314 0.06020 0.0076 0.0095 1.0000
9.000 0.8470 0.06538 0.06255 0.0128 0.0094 1.0000
9.250 0.8269 0.06726 0.06452 0.0190 0.0095 1.0000
9.500 0.7998 0.06846 0.06578 0.0262 0.0096 1.0000
9.750 0.7744 0.06998 0.06735 0.0322 0.0095 1.0000
10.000 0.7507 0.07211 0.06955 0.0368 0.0095 1.0000
10.250 0.7277 0.07497 0.07249 0.0401 0.0098 1.0000
10.500 0.7054 0.07823 0.07581 0.0422 0.0097 1.0000
10.750 0.6830 0.08221 0.07985 0.0432 0.0096 1.0000
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Polar data table (+)
Polar graphs
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