GOE 587 AIRFOIL (goe587-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 587 AIRFOIL (goe587-il) Reynolds number: 200,000 Max Cl/Cd: 62.89 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe587-il-200000-n5.txt Download as CSV file: xf-goe587-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 587 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4336 0.09061 0.08718 -0.0150 1.0000 0.0170
-7.500 -0.4337 0.08768 0.08430 -0.0161 1.0000 0.0173
-7.250 -0.4341 0.08471 0.08137 -0.0174 1.0000 0.0177
-7.000 -0.4295 0.08148 0.07817 -0.0198 1.0000 0.0186
-6.750 -0.4206 0.07851 0.07520 -0.0235 1.0000 0.0194
-6.500 -0.4108 0.07523 0.07190 -0.0261 1.0000 0.0197
-6.250 -0.3990 0.07191 0.06854 -0.0280 1.0000 0.0199
-6.000 -0.3873 0.06849 0.06508 -0.0292 1.0000 0.0199
-5.750 -0.3749 0.06500 0.06153 -0.0300 1.0000 0.0200
-5.500 -0.3622 0.06150 0.05798 -0.0304 1.0000 0.0201
-5.250 -0.3491 0.05798 0.05436 -0.0305 1.0000 0.0201
-5.000 -0.3362 0.05453 0.05082 -0.0302 1.0000 0.0201
-4.500 -0.3011 0.04379 0.03982 -0.0319 0.9945 0.0102
-4.000 -0.2359 0.03386 0.02930 -0.0371 0.9788 0.0114
-3.750 -0.2061 0.02974 0.02483 -0.0383 0.9690 0.0118
-3.500 -0.1753 0.02542 0.02007 -0.0385 0.9588 0.0113
-3.250 -0.1438 0.02154 0.01565 -0.0388 0.9491 0.0112
-3.000 -0.1101 0.01795 0.01140 -0.0396 0.9406 0.0115
-2.750 -0.0763 0.01558 0.00851 -0.0404 0.9307 0.0126
-2.500 -0.0408 0.01443 0.00709 -0.0418 0.9203 0.0166
-2.250 -0.0057 0.01290 0.00526 -0.0429 0.9091 0.0193
-2.000 0.0289 0.01212 0.00439 -0.0442 0.8955 0.0278
-1.750 0.0614 0.01155 0.00370 -0.0451 0.8798 0.0417
-1.500 0.0921 0.01119 0.00326 -0.0457 0.8627 0.0563
-1.250 0.1210 0.01090 0.00285 -0.0458 0.8447 0.0662
-1.000 0.1480 0.01065 0.00253 -0.0456 0.8254 0.0774
-0.750 0.1743 0.01043 0.00226 -0.0452 0.8065 0.0986
-0.500 0.1997 0.01020 0.00206 -0.0447 0.7881 0.1425
-0.250 0.2206 0.00949 0.00194 -0.0436 0.7701 0.3661
0.250 0.3616 0.00843 0.00207 -0.0606 0.7366 1.0000
0.500 0.3848 0.00851 0.00202 -0.0596 0.7182 1.0000
0.750 0.4079 0.00860 0.00199 -0.0587 0.7002 1.0000
1.000 0.4310 0.00869 0.00198 -0.0577 0.6823 1.0000
1.250 0.4535 0.00880 0.00197 -0.0566 0.6613 1.0000
1.500 0.4750 0.00893 0.00198 -0.0553 0.6298 1.0000
1.750 0.4968 0.00907 0.00200 -0.0540 0.6026 1.0000
2.000 0.5192 0.00920 0.00206 -0.0530 0.5838 1.0000
2.250 0.5415 0.00935 0.00214 -0.0519 0.5654 1.0000
2.500 0.5633 0.00952 0.00228 -0.0507 0.5429 1.0000
2.750 0.5854 0.00969 0.00242 -0.0496 0.5246 1.0000
3.000 0.6073 0.00988 0.00258 -0.0484 0.5054 1.0000
3.250 0.6287 0.01009 0.00276 -0.0472 0.4780 1.0000
3.500 0.6497 0.01033 0.00299 -0.0458 0.4392 1.0000
3.750 0.6689 0.01071 0.00320 -0.0442 0.3764 1.0000
4.000 0.6791 0.01205 0.00370 -0.0414 0.2009 1.0000
4.250 0.6901 0.01357 0.00452 -0.0388 0.0550 1.0000
4.500 0.7098 0.01415 0.00517 -0.0374 0.0417 1.0000
4.750 0.7285 0.01484 0.00602 -0.0357 0.0311 1.0000
5.000 0.7470 0.01558 0.00689 -0.0341 0.0217 1.0000
5.250 0.7628 0.01664 0.00802 -0.0320 0.0170 1.0000
5.500 0.7818 0.01738 0.00890 -0.0303 0.0135 1.0000
5.750 0.7979 0.01859 0.01021 -0.0282 0.0119 1.0000
6.000 0.8146 0.01996 0.01168 -0.0261 0.0108 1.0000
6.250 0.8307 0.02207 0.01394 -0.0242 0.0093 1.0000
6.500 0.8516 0.02370 0.01576 -0.0228 0.0081 1.0000
6.750 0.8730 0.02602 0.01835 -0.0213 0.0077 1.0000
7.000 0.8937 0.02867 0.02132 -0.0198 0.0075 1.0000
7.250 0.9122 0.03176 0.02479 -0.0179 0.0074 1.0000
7.500 0.9278 0.03496 0.02839 -0.0158 0.0074 1.0000
7.750 0.9401 0.03851 0.03235 -0.0135 0.0075 1.0000
8.000 0.9490 0.04220 0.03643 -0.0111 0.0077 1.0000
8.250 0.9544 0.04601 0.04060 -0.0086 0.0078 1.0000
8.500 0.9595 0.04944 0.04436 -0.0062 0.0074 1.0000
8.750 0.9622 0.05271 0.04792 -0.0040 0.0069 1.0000
9.000 0.9584 0.05650 0.05198 -0.0017 0.0071 1.0000
9.250 0.9525 0.05992 0.05562 0.0004 0.0069 1.0000
9.500 0.9375 0.06341 0.05929 0.0030 0.0074 1.0000
9.750 0.9285 0.06576 0.06177 0.0046 0.0064 1.0000
10.000 0.9107 0.06988 0.06605 0.0047 0.0066 1.0000
10.250 0.8898 0.07515 0.07144 0.0029 0.0072 1.0000
10.500 0.8713 0.08073 0.07713 -0.0004 0.0077 1.0000
11.000 0.8418 0.09415 0.09068 -0.0098 0.0081 1.0000
11.250 0.8271 0.10221 0.09874 -0.0149 0.0086 1.0000
11.500 0.8239 0.11022 0.10677 -0.0199 0.0084 1.0000
11.750 0.8207 0.12070 0.11723 -0.0251 0.0122 1.0000
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Polar data table (+)
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