GOE 491 AIRFOIL (goe491-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 491 AIRFOIL (goe491-il) Reynolds number: 100,000 Max Cl/Cd: 50.46 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe491-il-100000-n5.txt Download as CSV file: xf-goe491-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 491 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4863 0.12533 0.12010 -0.0010 1.0000 0.0333
-9.750 -0.4833 0.12259 0.11740 -0.0027 1.0000 0.0334
-9.500 -0.4815 0.11982 0.11468 -0.0047 1.0000 0.0335
-9.250 -0.4789 0.11698 0.11188 -0.0065 1.0000 0.0335
-9.000 -0.4764 0.11398 0.10893 -0.0082 1.0000 0.0336
-8.750 -0.4738 0.11094 0.10594 -0.0098 1.0000 0.0336
-8.500 -0.4721 0.10782 0.10287 -0.0114 1.0000 0.0337
-8.250 -0.4661 0.10326 0.09837 -0.0112 1.0000 0.0339
-8.000 -0.4572 0.09844 0.09356 -0.0099 1.0000 0.0343
-7.750 -0.4544 0.09515 0.09032 -0.0104 1.0000 0.0345
-7.500 -0.4516 0.09185 0.08707 -0.0112 1.0000 0.0346
-7.250 -0.4467 0.08858 0.08383 -0.0130 1.0000 0.0347
-7.000 -0.4409 0.08510 0.08038 -0.0149 1.0000 0.0347
-6.750 -0.4335 0.08159 0.07688 -0.0172 1.0000 0.0345
-6.500 -0.4261 0.07837 0.07366 -0.0164 1.0000 0.0360
-6.250 -0.4171 0.07513 0.07043 -0.0177 1.0000 0.0374
-5.250 -0.3604 0.05746 0.05241 -0.0268 1.0000 0.0245
-5.000 -0.3473 0.05398 0.04887 -0.0268 1.0000 0.0240
-4.750 -0.3315 0.05040 0.04518 -0.0271 1.0000 0.0236
-4.500 -0.3142 0.04669 0.04132 -0.0273 1.0000 0.0234
-4.250 -0.2960 0.04294 0.03738 -0.0272 1.0000 0.0232
-4.000 -0.2770 0.03914 0.03333 -0.0268 1.0000 0.0232
-3.750 -0.2574 0.03533 0.02922 -0.0260 1.0000 0.0235
-3.500 -0.2363 0.03087 0.02428 -0.0248 1.0000 0.0246
-3.250 -0.2173 0.02831 0.02144 -0.0236 1.0000 0.0260
-3.000 -0.1969 0.02597 0.01874 -0.0223 1.0000 0.0272
-2.750 -0.1750 0.02338 0.01570 -0.0208 1.0000 0.0288
-2.500 -0.1507 0.02057 0.01218 -0.0193 1.0000 0.0331
-2.250 -0.1290 0.01987 0.01137 -0.0182 1.0000 0.0380
-2.000 -0.1050 0.01834 0.00949 -0.0170 1.0000 0.0452
-1.750 -0.0749 0.01778 0.00872 -0.0175 0.9966 0.0595
-1.500 -0.0357 0.01738 0.00814 -0.0201 0.9882 0.0779
-1.250 0.0011 0.01673 0.00735 -0.0220 0.9797 0.0886
-1.000 0.0373 0.01601 0.00647 -0.0235 0.9704 0.0930
-0.750 0.0726 0.01540 0.00578 -0.0250 0.9600 0.0971
-0.500 0.1076 0.01485 0.00529 -0.0264 0.9487 0.1038
-0.250 0.1444 0.01441 0.00480 -0.0281 0.9373 0.1124
0.000 0.1837 0.01400 0.00437 -0.0303 0.9257 0.1216
0.250 0.2231 0.01363 0.00402 -0.0324 0.9116 0.1373
0.500 0.2601 0.01312 0.00379 -0.0342 0.8952 0.2085
1.000 0.3873 0.01114 0.00345 -0.0488 0.8577 1.0000
1.250 0.4198 0.01116 0.00335 -0.0494 0.8228 1.0000
1.500 0.4510 0.01121 0.00326 -0.0495 0.7811 1.0000
1.750 0.4803 0.01133 0.00321 -0.0493 0.7355 1.0000
2.000 0.5072 0.01153 0.00320 -0.0486 0.6887 1.0000
2.250 0.5322 0.01181 0.00325 -0.0476 0.6398 1.0000
2.500 0.5556 0.01214 0.00337 -0.0464 0.5932 1.0000
2.750 0.5787 0.01248 0.00352 -0.0452 0.5543 1.0000
3.000 0.6018 0.01281 0.00372 -0.0441 0.5228 1.0000
3.250 0.6242 0.01318 0.00392 -0.0429 0.4894 1.0000
3.500 0.6464 0.01357 0.00419 -0.0416 0.4588 1.0000
3.750 0.6689 0.01394 0.00447 -0.0405 0.4322 1.0000
4.000 0.6921 0.01429 0.00480 -0.0395 0.4136 1.0000
4.250 0.7156 0.01460 0.00517 -0.0386 0.3962 1.0000
4.500 0.7386 0.01492 0.00557 -0.0376 0.3738 1.0000
4.750 0.7612 0.01524 0.00594 -0.0365 0.3465 1.0000
5.000 0.7838 0.01558 0.00632 -0.0355 0.3168 1.0000
5.250 0.8058 0.01597 0.00671 -0.0344 0.2800 1.0000
5.500 0.8266 0.01653 0.00718 -0.0331 0.2312 1.0000
5.750 0.8468 0.01728 0.00779 -0.0319 0.1832 1.0000
6.000 0.8654 0.01834 0.00862 -0.0305 0.1204 1.0000
6.250 0.8827 0.01965 0.00965 -0.0289 0.0782 1.0000
6.500 0.9017 0.02071 0.01080 -0.0274 0.0657 1.0000
6.750 0.9199 0.02181 0.01200 -0.0258 0.0548 1.0000
7.000 0.9363 0.02312 0.01346 -0.0241 0.0452 1.0000
7.250 0.9496 0.02484 0.01523 -0.0220 0.0383 1.0000
7.500 0.9657 0.02629 0.01688 -0.0201 0.0323 1.0000
7.750 0.9780 0.02865 0.01924 -0.0179 0.0286 1.0000
8.000 0.9967 0.03010 0.02105 -0.0163 0.0248 1.0000
8.250 1.0133 0.03216 0.02336 -0.0146 0.0220 1.0000
8.500 1.0288 0.03449 0.02593 -0.0129 0.0203 1.0000
8.750 1.0414 0.03702 0.02863 -0.0113 0.0188 1.0000
9.000 1.0508 0.04027 0.03221 -0.0093 0.0174 1.0000
9.250 1.0596 0.04294 0.03537 -0.0071 0.0164 1.0000
9.500 1.0634 0.04625 0.03923 -0.0048 0.0160 1.0000
9.750 1.0620 0.04976 0.04316 -0.0024 0.0157 1.0000
10.000 1.0555 0.05335 0.04712 0.0001 0.0155 1.0000
10.250 1.0434 0.05675 0.05081 0.0028 0.0155 1.0000
10.500 1.0278 0.06020 0.05451 0.0048 0.0154 1.0000
10.750 1.0112 0.06414 0.05865 0.0050 0.0155 1.0000
11.000 0.9926 0.06902 0.06374 0.0034 0.0155 1.0000
11.250 0.9740 0.07494 0.06982 -0.0003 0.0156 1.0000
11.500 0.9570 0.08167 0.07658 -0.0052 0.0158 1.0000
11.750 0.9401 0.08941 0.08441 -0.0109 0.0161 1.0000
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Polar data table (+)
Polar graphs
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