LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-080 (lwk80080-il) Reynolds number: 50,000 Max Cl/Cd: 24.68 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80080-il-50000-n5.txt Download as CSV file: xf-lwk80080-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6381 0.09516 0.08818 -0.0122 1.0000 0.0412
-9.500 -0.6437 0.08912 0.08220 -0.0163 1.0000 0.0407
-9.250 -0.6524 0.08348 0.07658 -0.0200 1.0000 0.0401
-9.000 -0.6633 0.07863 0.07173 -0.0224 1.0000 0.0395
-8.750 -0.6762 0.07428 0.06736 -0.0230 1.0000 0.0390
-8.500 -0.6865 0.06993 0.06291 -0.0233 1.0000 0.0387
-8.250 -0.6935 0.06566 0.05847 -0.0231 1.0000 0.0383
-8.000 -0.6977 0.06139 0.05399 -0.0224 1.0000 0.0380
-7.750 -0.6985 0.05719 0.04949 -0.0213 1.0000 0.0377
-7.500 -0.6957 0.05320 0.04517 -0.0200 1.0000 0.0378
-7.250 -0.6899 0.04935 0.04092 -0.0185 1.0000 0.0380
-7.000 -0.6813 0.04569 0.03680 -0.0167 1.0000 0.0393
-6.750 -0.6696 0.04251 0.03310 -0.0149 1.0000 0.0419
-6.500 -0.6549 0.03958 0.02950 -0.0130 1.0000 0.0442
-6.250 -0.6380 0.03650 0.02611 -0.0117 1.0000 0.0463
-6.000 -0.6180 0.03389 0.02321 -0.0104 1.0000 0.0484
-5.750 -0.5953 0.03152 0.02043 -0.0092 1.0000 0.0516
-5.500 -0.5716 0.02957 0.01811 -0.0081 1.0000 0.0587
-5.250 -0.5479 0.02785 0.01630 -0.0072 1.0000 0.0667
-5.000 -0.5219 0.02604 0.01435 -0.0062 1.0000 0.0741
-4.750 -0.5005 0.02474 0.01301 -0.0050 1.0000 0.0910
-4.500 -0.4807 0.02340 0.01160 -0.0033 1.0000 0.1079
-4.250 -0.4638 0.02208 0.01040 -0.0016 1.0000 0.1368
-4.000 -0.4499 0.02050 0.00920 0.0004 1.0000 0.1959
-3.750 -0.4466 0.01839 0.00833 0.0040 1.0000 0.3766
-3.500 -0.4361 0.01767 0.00912 0.0104 1.0000 0.7043
-3.250 -0.4210 0.01798 0.00930 0.0150 1.0000 0.7930
-3.000 -0.3843 0.01862 0.00969 0.0167 1.0000 0.8661
-2.750 -0.2706 0.01959 0.00979 0.0041 1.0000 0.9303
-2.500 -0.2149 0.01938 0.00922 -0.0014 1.0000 0.9483
-2.250 -0.1717 0.01905 0.00864 -0.0050 1.0000 0.9613
-2.000 -0.1325 0.01872 0.00808 -0.0080 1.0000 0.9726
-1.750 -0.0956 0.01840 0.00762 -0.0107 1.0000 0.9826
-1.500 -0.0588 0.01807 0.00718 -0.0134 1.0000 0.9918
-1.250 -0.0245 0.01782 0.00685 -0.0158 1.0000 1.0000
-1.000 -0.0147 0.01770 0.00674 -0.0134 1.0000 1.0000
-0.750 -0.0072 0.01763 0.00665 -0.0107 1.0000 1.0000
-0.500 -0.0027 0.01760 0.00665 -0.0075 1.0000 1.0000
-0.250 -0.0006 0.01759 0.00664 -0.0039 1.0000 1.0000
0.000 0.0000 0.01758 0.00663 0.0000 1.0000 1.0000
0.250 0.0007 0.01759 0.00664 0.0039 1.0000 1.0000
0.500 0.0027 0.01759 0.00664 0.0075 1.0000 1.0000
0.750 0.0072 0.01763 0.00666 0.0107 1.0000 1.0000
1.000 0.0147 0.01770 0.00672 0.0134 1.0000 1.0000
1.250 0.0246 0.01782 0.00685 0.0158 1.0000 1.0000
1.500 0.0583 0.01807 0.00718 0.0135 0.9920 1.0000
1.750 0.0957 0.01840 0.00762 0.0107 0.9826 1.0000
2.000 0.1327 0.01872 0.00808 0.0079 0.9725 1.0000
2.250 0.1717 0.01905 0.00865 0.0050 0.9614 1.0000
2.500 0.2154 0.01937 0.00921 0.0013 0.9481 1.0000
2.750 0.2699 0.01959 0.00980 -0.0040 0.9305 1.0000
3.000 0.3849 0.01860 0.00967 -0.0167 0.8649 1.0000
3.250 0.4208 0.01799 0.00933 -0.0150 0.7944 1.0000
3.500 0.4363 0.01768 0.00913 -0.0105 0.7068 1.0000
3.750 0.4471 0.01834 0.00835 -0.0041 0.3827 1.0000
4.000 0.4501 0.02047 0.00919 -0.0004 0.1975 1.0000
4.250 0.4638 0.02208 0.01040 0.0015 0.1352 1.0000
4.500 0.4806 0.02340 0.01163 0.0033 0.1072 1.0000
4.750 0.5005 0.02478 0.01305 0.0050 0.0896 1.0000
5.000 0.5219 0.02607 0.01438 0.0062 0.0737 1.0000
5.250 0.5482 0.02791 0.01639 0.0072 0.0660 1.0000
5.500 0.5709 0.02967 0.01817 0.0081 0.0567 1.0000
5.750 0.5953 0.03157 0.02050 0.0093 0.0511 1.0000
6.000 0.6176 0.03398 0.02320 0.0104 0.0476 1.0000
6.250 0.6376 0.03662 0.02618 0.0116 0.0457 1.0000
6.500 0.6546 0.03960 0.02960 0.0132 0.0435 1.0000
6.750 0.6690 0.04259 0.03324 0.0151 0.0406 1.0000
7.000 0.6808 0.04573 0.03686 0.0168 0.0384 1.0000
7.250 0.6897 0.04935 0.04091 0.0185 0.0377 1.0000
7.500 0.6955 0.05324 0.04521 0.0200 0.0376 1.0000
7.750 0.6986 0.05718 0.04948 0.0213 0.0377 1.0000
8.000 0.6985 0.06123 0.05381 0.0223 0.0380 1.0000
8.250 0.6943 0.06553 0.05834 0.0230 0.0384 1.0000
8.500 0.6861 0.07003 0.06301 0.0232 0.0386 1.0000
8.750 0.6769 0.07423 0.06731 0.0230 0.0391 1.0000
9.000 0.6639 0.07857 0.07166 0.0223 0.0394 1.0000
9.250 0.6526 0.08351 0.07661 0.0199 0.0400 1.0000
9.500 0.6445 0.08904 0.08212 0.0163 0.0407 1.0000
9.750 0.6392 0.09499 0.08801 0.0122 0.0412 1.0000
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Polar data table (+)
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