LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-100 (lwk80100-il) Reynolds number: 500,000 Max Cl/Cd: 49.01 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80100-il-500000.txt Download as CSV file: xf-lwk80100-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-100
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7135 0.09312 0.09094 -0.0086 1.0000 0.0155
-11.500 -0.7303 0.08654 0.08440 -0.0128 1.0000 0.0145
-11.250 -0.7737 0.06822 0.06593 -0.0274 1.0000 0.0138
-11.000 -0.8100 0.05945 0.05697 -0.0323 1.0000 0.0133
-10.750 -0.9390 0.04052 0.03699 -0.0288 1.0000 0.0114
-10.500 -0.8805 0.04648 0.04343 -0.0311 1.0000 0.0129
-10.250 -0.8997 0.04245 0.03912 -0.0274 1.0000 0.0130
-10.000 -0.9352 0.03404 0.02991 -0.0217 1.0000 0.0121
-9.750 -0.9319 0.03105 0.02659 -0.0191 1.0000 0.0123
-9.500 -0.9214 0.02907 0.02439 -0.0172 1.0000 0.0126
-9.250 -0.9093 0.02703 0.02210 -0.0153 1.0000 0.0128
-9.000 -0.8944 0.02539 0.02026 -0.0136 1.0000 0.0134
-8.750 -0.8767 0.02430 0.01901 -0.0123 1.0000 0.0143
-8.500 -0.8599 0.02263 0.01712 -0.0107 1.0000 0.0146
-8.250 -0.8418 0.02116 0.01546 -0.0093 1.0000 0.0149
-8.000 -0.8216 0.02046 0.01461 -0.0081 1.0000 0.0154
-7.750 -0.8088 0.01796 0.01189 -0.0058 1.0000 0.0162
-7.500 -0.7896 0.01681 0.01069 -0.0048 0.9915 0.0173
-7.250 -0.7561 0.01592 0.00974 -0.0066 0.9834 0.0184
-7.000 -0.7210 0.01521 0.00896 -0.0086 0.9765 0.0206
-6.750 -0.6863 0.01412 0.00776 -0.0106 0.9701 0.0237
-6.500 -0.6502 0.01345 0.00706 -0.0129 0.9635 0.0275
-6.250 -0.6130 0.01281 0.00633 -0.0154 0.9574 0.0317
-6.000 -0.5786 0.01219 0.00570 -0.0173 0.9494 0.0383
-5.750 -0.5446 0.01168 0.00514 -0.0190 0.9423 0.0450
-5.500 -0.5152 0.01139 0.00481 -0.0196 0.9341 0.0524
-5.250 -0.4871 0.01096 0.00438 -0.0200 0.9272 0.0626
-5.000 -0.4635 0.01061 0.00405 -0.0194 0.9195 0.0755
-4.750 -0.4377 0.01029 0.00375 -0.0192 0.9135 0.0938
-4.500 -0.4161 0.00989 0.00347 -0.0181 0.9071 0.1235
-4.250 -0.3949 0.00941 0.00320 -0.0171 0.9015 0.1785
-4.000 -0.3764 0.00878 0.00294 -0.0157 0.8960 0.2686
-3.750 -0.3603 0.00809 0.00268 -0.0137 0.8902 0.3798
-3.500 -0.3465 0.00732 0.00244 -0.0112 0.8853 0.5131
-3.250 -0.3328 0.00681 0.00241 -0.0082 0.8802 0.6381
-3.000 -0.3102 0.00675 0.00245 -0.0069 0.8759 0.6865
-2.750 -0.2854 0.00677 0.00249 -0.0061 0.8722 0.7151
-2.500 -0.2597 0.00682 0.00252 -0.0055 0.8689 0.7326
-2.250 -0.2346 0.00686 0.00255 -0.0048 0.8648 0.7474
-2.000 -0.2088 0.00692 0.00259 -0.0042 0.8611 0.7604
-1.750 -0.1825 0.00698 0.00261 -0.0038 0.8578 0.7704
-1.500 -0.1561 0.00706 0.00268 -0.0033 0.8547 0.7803
-1.250 -0.1307 0.00713 0.00277 -0.0026 0.8509 0.7910
-1.000 -0.1052 0.00721 0.00286 -0.0019 0.8471 0.8018
-0.750 -0.0789 0.00729 0.00292 -0.0014 0.8437 0.8108
-0.500 -0.0519 0.00735 0.00300 -0.0011 0.8405 0.8180
-0.250 -0.0268 0.00738 0.00304 -0.0004 0.8356 0.8253
0.000 0.0000 0.00738 0.00304 0.0000 0.8308 0.8307
0.250 0.0269 0.00739 0.00304 0.0004 0.8254 0.8356
0.500 0.0519 0.00734 0.00299 0.0011 0.8177 0.8404
0.750 0.0789 0.00729 0.00292 0.0014 0.8107 0.8437
1.000 0.1052 0.00721 0.00286 0.0019 0.8018 0.8471
1.250 0.1309 0.00714 0.00278 0.0026 0.7916 0.8509
1.500 0.1560 0.00705 0.00267 0.0034 0.7794 0.8548
1.750 0.1825 0.00698 0.00260 0.0038 0.7700 0.8579
2.000 0.2087 0.00691 0.00258 0.0043 0.7593 0.8611
2.250 0.2346 0.00686 0.00255 0.0048 0.7469 0.8648
2.500 0.2597 0.00682 0.00252 0.0055 0.7318 0.8689
2.750 0.2855 0.00677 0.00249 0.0061 0.7160 0.8722
3.000 0.3108 0.00675 0.00247 0.0068 0.6915 0.8758
3.250 0.3333 0.00680 0.00242 0.0081 0.6419 0.8802
3.500 0.3475 0.00728 0.00243 0.0110 0.5216 0.8853
3.750 0.3606 0.00807 0.00268 0.0137 0.3819 0.8902
4.000 0.3762 0.00880 0.00295 0.0157 0.2660 0.8961
4.250 0.3951 0.00940 0.00320 0.0171 0.1798 0.9015
4.500 0.4164 0.00988 0.00346 0.0181 0.1251 0.9071
4.750 0.4381 0.01026 0.00373 0.0191 0.0963 0.9135
5.000 0.4636 0.01060 0.00405 0.0194 0.0775 0.9196
5.250 0.4873 0.01094 0.00436 0.0200 0.0644 0.9273
5.500 0.5155 0.01136 0.00478 0.0196 0.0526 0.9341
5.750 0.5449 0.01164 0.00509 0.0190 0.0444 0.9422
6.000 0.5791 0.01211 0.00562 0.0172 0.0378 0.9493
6.250 0.6126 0.01290 0.00642 0.0154 0.0305 0.9575
6.500 0.6509 0.01333 0.00692 0.0129 0.0261 0.9633
6.750 0.6842 0.01463 0.00830 0.0110 0.0217 0.9706
7.000 0.7217 0.01510 0.00884 0.0085 0.0195 0.9764
7.250 0.7564 0.01587 0.00967 0.0065 0.0180 0.9834
7.500 0.7892 0.01692 0.01077 0.0048 0.0165 0.9918
7.750 0.8054 0.01880 0.01279 0.0064 0.0157 1.0000
8.000 0.8218 0.02041 0.01457 0.0081 0.0152 1.0000
8.250 0.8410 0.02147 0.01581 0.0095 0.0149 1.0000
8.500 0.8591 0.02292 0.01745 0.0110 0.0143 1.0000
8.750 0.8752 0.02478 0.01954 0.0126 0.0141 1.0000
9.000 0.8914 0.02625 0.02122 0.0142 0.0135 1.0000
9.250 0.9056 0.02796 0.02315 0.0159 0.0130 1.0000
9.500 0.9166 0.03010 0.02554 0.0179 0.0126 1.0000
9.750 0.9224 0.03291 0.02867 0.0203 0.0125 1.0000
10.000 0.9239 0.03596 0.03205 0.0229 0.0124 1.0000
10.250 0.8879 0.04405 0.04083 0.0283 0.0131 1.0000
10.500 0.8550 0.04954 0.04664 0.0323 0.0138 1.0000
10.750 0.8301 0.05444 0.05177 0.0333 0.0138 1.0000
11.000 0.8042 0.06024 0.05776 0.0319 0.0138 1.0000
11.250 0.7740 0.06795 0.06564 0.0274 0.0142 1.0000
11.500 0.5486 0.08516 0.08307 0.0195 0.0197 1.0000
11.750 0.5760 0.08177 0.07970 0.0209 0.0170 1.0000
12.000 0.5662 0.08758 0.08550 0.0186 0.0167 1.0000
12.250 0.5650 0.09082 0.08873 0.0173 0.0162 1.0000
13.250 0.6564 0.14458 0.14224 -0.0147 0.0205 1.0000
13.500 0.4760 0.12429 0.12215 0.0060 0.0220 1.0000
13.750 0.4746 0.12797 0.12583 0.0042 0.0220 1.0000
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Polar data table (+)
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