LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 79-100 (lwk79100-il) Reynolds number: 100,000 Max Cl/Cd: 37.36 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk79100-il-100000.txt Download as CSV file: xf-lwk79100-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LWK 79-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5968 0.11537 0.11071 0.0127 1.0000 0.1537
-10.500 -0.7428 0.09516 0.09025 0.0003 1.0000 0.0976
-10.250 -0.8268 0.07223 0.06716 -0.0158 1.0000 0.0705
-10.000 -0.8428 0.06736 0.06221 -0.0168 1.0000 0.0695
-9.750 -0.8601 0.06235 0.05703 -0.0172 1.0000 0.0685
-9.500 -0.8734 0.05716 0.05156 -0.0173 1.0000 0.0678
-9.250 -0.8806 0.05225 0.04628 -0.0170 1.0000 0.0678
-9.000 -0.8812 0.04780 0.04136 -0.0162 1.0000 0.0686
-8.750 -0.8767 0.04365 0.03666 -0.0152 1.0000 0.0698
-8.500 -0.8666 0.03992 0.03234 -0.0140 1.0000 0.0707
-8.250 -0.8532 0.03644 0.02830 -0.0129 1.0000 0.0724
-8.000 -0.8331 0.03396 0.02587 -0.0125 1.0000 0.0768
-7.750 -0.8126 0.03173 0.02332 -0.0116 1.0000 0.0807
-7.500 -0.7913 0.02970 0.02073 -0.0105 1.0000 0.0844
-7.250 -0.7686 0.02749 0.01860 -0.0101 1.0000 0.0903
-7.000 -0.7446 0.02586 0.01671 -0.0093 1.0000 0.0964
-6.750 -0.7208 0.02410 0.01500 -0.0087 1.0000 0.1037
-6.500 -0.6968 0.02270 0.01348 -0.0079 1.0000 0.1135
-6.250 -0.6728 0.02140 0.01215 -0.0071 1.0000 0.1252
-6.000 -0.6503 0.02003 0.01097 -0.0063 1.0000 0.1424
-5.750 -0.6280 0.01880 0.00986 -0.0054 1.0000 0.1682
-5.500 -0.6074 0.01749 0.00890 -0.0044 1.0000 0.2061
-5.250 -0.5872 0.01626 0.00803 -0.0033 1.0000 0.2599
-5.000 -0.5668 0.01529 0.00745 -0.0022 1.0000 0.3264
-4.750 -0.5459 0.01461 0.00714 -0.0009 1.0000 0.3965
-4.500 -0.5241 0.01427 0.00705 0.0005 1.0000 0.4596
-4.250 -0.5015 0.01419 0.00709 0.0021 1.0000 0.5095
-4.000 -0.4784 0.01423 0.00716 0.0035 1.0000 0.5500
-3.750 -0.4553 0.01427 0.00724 0.0051 1.0000 0.5821
-3.500 -0.4323 0.01428 0.00725 0.0066 1.0000 0.6106
-3.250 -0.4096 0.01423 0.00726 0.0082 1.0000 0.6339
-3.000 -0.3874 0.01413 0.00718 0.0097 1.0000 0.6574
-2.750 -0.3660 0.01400 0.00711 0.0113 1.0000 0.6780
-2.500 -0.3460 0.01384 0.00698 0.0129 1.0000 0.6992
-2.250 -0.3293 0.01369 0.00690 0.0148 1.0000 0.7179
-2.000 -0.3182 0.01361 0.00689 0.0173 1.0000 0.7358
-1.750 -0.3043 0.01359 0.00690 0.0190 0.9983 0.7546
-1.500 -0.2561 0.01360 0.00690 0.0148 0.9810 0.7770
-1.250 -0.2106 0.01354 0.00688 0.0115 0.9650 0.7979
-1.000 -0.1648 0.01347 0.00682 0.0082 0.9506 0.8196
-0.750 -0.1217 0.01339 0.00679 0.0058 0.9360 0.8388
-0.500 -0.0800 0.01332 0.00674 0.0036 0.9210 0.8568
-0.250 -0.0395 0.01327 0.00670 0.0017 0.9056 0.8736
0.000 0.0000 0.01325 0.00668 0.0000 0.8898 0.8898
0.250 0.0396 0.01327 0.00670 -0.0017 0.8736 0.9056
0.500 0.0800 0.01332 0.00674 -0.0036 0.8568 0.9210
0.750 0.1217 0.01339 0.00678 -0.0058 0.8387 0.9360
1.000 0.1648 0.01347 0.00682 -0.0082 0.8196 0.9506
1.250 0.2106 0.01354 0.00688 -0.0115 0.7979 0.9651
1.500 0.2562 0.01359 0.00690 -0.0148 0.7772 0.9811
1.750 0.3044 0.01359 0.00690 -0.0190 0.7546 0.9984
2.000 0.3181 0.01361 0.00689 -0.0173 0.7358 1.0000
2.250 0.3292 0.01369 0.00690 -0.0148 0.7179 1.0000
2.500 0.3459 0.01384 0.00698 -0.0128 0.6992 1.0000
2.750 0.3659 0.01400 0.00711 -0.0113 0.6780 1.0000
3.000 0.3873 0.01413 0.00718 -0.0096 0.6574 1.0000
3.250 0.4095 0.01423 0.00726 -0.0082 0.6339 1.0000
3.500 0.4322 0.01428 0.00725 -0.0065 0.6105 1.0000
3.750 0.4552 0.01427 0.00724 -0.0051 0.5821 1.0000
4.000 0.4784 0.01423 0.00716 -0.0035 0.5501 1.0000
4.250 0.5014 0.01419 0.00709 -0.0021 0.5095 1.0000
4.500 0.5240 0.01427 0.00705 -0.0005 0.4595 1.0000
4.750 0.5458 0.01461 0.00714 0.0009 0.3965 1.0000
5.000 0.5667 0.01529 0.00745 0.0022 0.3264 1.0000
5.250 0.5872 0.01626 0.00803 0.0033 0.2599 1.0000
5.500 0.6074 0.01749 0.00890 0.0044 0.2062 1.0000
5.750 0.6280 0.01880 0.00986 0.0054 0.1682 1.0000
6.000 0.6504 0.02003 0.01097 0.0063 0.1423 1.0000
6.250 0.6728 0.02141 0.01215 0.0071 0.1251 1.0000
6.500 0.6969 0.02270 0.01348 0.0079 0.1134 1.0000
6.750 0.7209 0.02410 0.01500 0.0087 0.1035 1.0000
7.000 0.7447 0.02586 0.01672 0.0093 0.0963 1.0000
7.250 0.7687 0.02750 0.01861 0.0101 0.0903 1.0000
7.500 0.7914 0.02969 0.02073 0.0105 0.0844 1.0000
7.750 0.8127 0.03174 0.02333 0.0116 0.0807 1.0000
8.000 0.8332 0.03397 0.02588 0.0125 0.0768 1.0000
8.250 0.8533 0.03648 0.02833 0.0129 0.0724 1.0000
8.500 0.8668 0.03993 0.03235 0.0140 0.0707 1.0000
8.750 0.8768 0.04369 0.03670 0.0152 0.0697 1.0000
9.000 0.8816 0.04782 0.04138 0.0162 0.0687 1.0000
9.250 0.8807 0.05233 0.04635 0.0169 0.0680 1.0000
9.500 0.8736 0.05720 0.05160 0.0173 0.0678 1.0000
9.750 0.8608 0.06238 0.05706 0.0171 0.0686 1.0000
10.000 0.8442 0.06735 0.06220 0.0167 0.0696 1.0000
10.250 0.8275 0.07229 0.06721 0.0157 0.0705 1.0000
10.500 0.7530 0.09378 0.08893 0.0014 0.0986 1.0000
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Polar data table (+)
Polar graphs
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