GOE 587 AIRFOIL (goe587-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 587 AIRFOIL (goe587-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.06 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe587-il-1000000-n5.txt Download as CSV file: xf-goe587-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4278 0.08978 0.08822 -0.0147 1.0000 0.0046
-7.500 -0.4290 0.08695 0.08541 -0.0155 1.0000 0.0046
-7.250 -0.4298 0.08378 0.08227 -0.0168 1.0000 0.0046
-7.000 -0.4255 0.08032 0.07881 -0.0187 1.0000 0.0046
-6.750 -0.4194 0.07699 0.07548 -0.0204 1.0000 0.0046
-6.500 -0.4068 0.07270 0.07117 -0.0238 0.9990 0.0046
-6.250 -0.3875 0.06786 0.06630 -0.0286 0.9935 0.0045
-6.000 -0.3717 0.06230 0.06068 -0.0329 0.9849 0.0042
-5.750 -0.3514 0.05716 0.05548 -0.0373 0.9723 0.0037
-5.500 -0.3151 0.05148 0.04967 -0.0444 0.9569 0.0033
-5.250 -0.2673 0.04492 0.04288 -0.0534 0.9372 0.0029
-5.000 -0.2304 0.03939 0.03706 -0.0583 0.9034 0.0026
-4.750 -0.2097 0.03532 0.03269 -0.0583 0.8742 0.0025
-4.500 -0.1904 0.03109 0.02817 -0.0574 0.8504 0.0024
-4.250 -0.1717 0.02588 0.02257 -0.0555 0.8288 0.0022
-4.000 -0.1644 0.01120 0.00626 -0.0490 0.8124 0.0018
-3.750 -0.1408 0.00998 0.00466 -0.0479 0.7911 0.0017
-3.500 -0.1166 0.00920 0.00355 -0.0470 0.7708 0.0018
-3.250 -0.0922 0.00863 0.00273 -0.0461 0.7527 0.0018
-3.000 -0.0669 0.00832 0.00226 -0.0455 0.7369 0.0020
-2.750 -0.0409 0.00818 0.00209 -0.0450 0.7231 0.0032
-2.500 -0.0131 0.00858 0.00262 -0.0452 0.7095 0.0042
-2.250 0.0114 0.00802 0.00183 -0.0444 0.6968 0.0077
-2.000 0.0418 0.00925 0.00323 -0.0453 0.6831 0.0122
-1.750 0.0660 0.00856 0.00243 -0.0447 0.6696 0.0145
-1.500 0.0914 0.00823 0.00198 -0.0441 0.6547 0.0139
-1.250 0.1170 0.00802 0.00163 -0.0436 0.6370 0.0133
-1.000 0.1426 0.00791 0.00140 -0.0431 0.6151 0.0129
-0.750 0.1682 0.00782 0.00121 -0.0427 0.5928 0.0127
-0.500 0.1939 0.00774 0.00104 -0.0423 0.5745 0.0125
0.000 0.2461 0.00761 0.00076 -0.0416 0.5483 0.0125
0.250 0.2725 0.00757 0.00063 -0.0414 0.5376 0.0133
0.500 0.2989 0.00755 0.00058 -0.0411 0.5261 0.0189
0.750 0.3247 0.00752 0.00059 -0.0408 0.5093 0.0504
1.000 0.3506 0.00754 0.00061 -0.0405 0.4925 0.0700
1.250 0.3762 0.00748 0.00065 -0.0402 0.4767 0.1285
1.500 0.3803 0.00557 0.00079 -0.0356 0.4647 0.8964
1.750 0.4034 0.00560 0.00089 -0.0344 0.4509 0.9338
2.000 0.4290 0.00571 0.00094 -0.0340 0.4286 0.9429
2.500 0.4793 0.00622 0.00113 -0.0331 0.3417 0.9628
2.750 0.5035 0.00687 0.00136 -0.0328 0.2442 0.9688
3.000 0.5245 0.00817 0.00189 -0.0322 0.0370 0.9768
3.250 0.5587 0.00838 0.00213 -0.0338 0.0306 0.9814
3.500 0.5878 0.00854 0.00228 -0.0343 0.0268 0.9836
3.750 0.6170 0.00876 0.00241 -0.0349 0.0143 0.9867
4.000 0.6476 0.00909 0.00268 -0.0357 0.0027 0.9880
4.250 0.6770 0.00933 0.00299 -0.0363 0.0024 0.9892
4.500 0.7058 0.00962 0.00335 -0.0367 0.0023 0.9907
4.750 0.7341 0.00996 0.00375 -0.0370 0.0023 0.9926
5.000 0.7613 0.01039 0.00427 -0.0371 0.0023 0.9947
5.250 0.7889 0.01096 0.00493 -0.0373 0.0024 0.9970
5.500 0.8156 0.01171 0.00589 -0.0373 0.0025 0.9994
5.750 0.8342 0.01256 0.00687 -0.0355 0.0026 1.0000
6.000 0.8496 0.01351 0.00795 -0.0331 0.0027 1.0000
6.250 0.8655 0.01462 0.00919 -0.0308 0.0028 1.0000
6.500 0.8815 0.01621 0.01095 -0.0284 0.0030 1.0000
6.750 0.8996 0.01832 0.01325 -0.0263 0.0031 1.0000
7.000 0.9191 0.02053 0.01567 -0.0246 0.0030 1.0000
7.250 0.9387 0.02233 0.01766 -0.0232 0.0026 1.0000
7.500 0.9579 0.02334 0.01882 -0.0221 0.0022 1.0000
7.750 0.9741 0.02661 0.02236 -0.0200 0.0021 1.0000
8.000 0.9895 0.02871 0.02468 -0.0183 0.0019 1.0000
8.250 1.0015 0.03192 0.02817 -0.0160 0.0018 1.0000
8.500 1.0109 0.03437 0.03087 -0.0139 0.0016 1.0000
8.750 0.9820 0.04492 0.04210 -0.0072 0.0012 1.0000
9.000 0.9994 0.04607 0.04333 -0.0063 0.0011 1.0000
9.250 1.0019 0.04919 0.04662 -0.0041 0.0010 1.0000
9.500 1.0019 0.05224 0.04983 -0.0019 0.0009 1.0000
9.750 0.9905 0.05584 0.05359 0.0011 0.0009 1.0000
10.000 0.9621 0.05966 0.05757 0.0053 0.0010 1.0000
10.250 0.9439 0.06306 0.06108 0.0065 0.0010 1.0000
10.500 0.9390 0.06578 0.06388 0.0064 0.0009 1.0000
10.750 0.9243 0.07011 0.06830 0.0049 0.0008 1.0000
11.000 0.9026 0.07624 0.07454 0.0011 0.0008 1.0000
11.250 0.8791 0.08423 0.08262 -0.0049 0.0009 1.0000
11.500 0.8393 0.10157 0.10002 -0.0173 0.0012 1.0000
11.750 0.8397 0.10760 0.10604 -0.0205 0.0011 1.0000
12.000 0.8396 0.11229 0.11074 -0.0230 0.0013 1.0000
12.250 0.7276 0.11624 0.11485 -0.0245 0.0019 1.0000
12.500 0.7211 0.12225 0.12086 -0.0275 0.0019 1.0000
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Polar data table (+)
Polar graphs
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