LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-080 (lwk80080-il) Reynolds number: 100,000 Max Cl/Cd: 37.42 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80080-il-100000.txt Download as CSV file: xf-lwk80080-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6271 0.09993 0.09510 -0.0040 1.0000 0.1050
-9.250 -0.6337 0.09531 0.09053 -0.0076 1.0000 0.1080
-9.000 -0.6467 0.08997 0.08527 -0.0133 1.0000 0.1093
-8.750 -0.6737 0.08521 0.08053 -0.0186 1.0000 0.1103
-8.500 -0.6549 0.08153 0.07692 -0.0158 1.0000 0.1204
-8.250 -0.6777 0.07748 0.07282 -0.0186 1.0000 0.1231
-8.000 -0.6937 0.07363 0.06880 -0.0201 1.0000 0.1241
-7.750 -0.6820 0.06971 0.06497 -0.0186 1.0000 0.1361
-6.500 -0.6641 0.04401 0.03732 -0.0146 1.0000 0.0827
-6.250 -0.6500 0.03783 0.03065 -0.0122 1.0000 0.0650
-6.000 -0.6337 0.03452 0.02628 -0.0087 1.0000 0.0572
-5.750 -0.6161 0.03092 0.02235 -0.0069 1.0000 0.0564
-5.500 -0.5964 0.02823 0.01923 -0.0049 1.0000 0.0567
-5.250 -0.5754 0.02564 0.01628 -0.0033 1.0000 0.0585
-5.000 -0.5550 0.02384 0.01449 -0.0022 1.0000 0.0657
-4.750 -0.5319 0.02179 0.01221 -0.0006 1.0000 0.0726
-4.500 -0.5112 0.02053 0.01088 0.0009 1.0000 0.0833
-4.250 -0.4921 0.01906 0.00949 0.0027 1.0000 0.0969
-4.000 -0.4772 0.01758 0.00821 0.0051 1.0000 0.1152
-3.750 -0.4647 0.01642 0.00727 0.0079 1.0000 0.1500
-3.500 -0.4594 0.01455 0.00622 0.0118 1.0000 0.2561
-3.250 -0.4711 0.01260 0.00666 0.0210 1.0000 0.7248
-3.000 -0.4634 0.01302 0.00713 0.0274 1.0000 0.8231
-2.750 -0.4412 0.01351 0.00751 0.0312 1.0000 0.8814
-2.500 -0.2435 0.01557 0.00865 0.0051 1.0000 0.9504
-2.250 -0.1449 0.01543 0.00812 -0.0083 1.0000 0.9756
-2.000 -0.0878 0.01500 0.00747 -0.0149 1.0000 0.9894
-1.750 -0.0341 0.01448 0.00682 -0.0211 1.0000 0.9996
-1.500 -0.0173 0.01423 0.00655 -0.0201 1.0000 1.0000
-1.250 -0.0042 0.01405 0.00638 -0.0184 1.0000 1.0000
-1.000 0.0060 0.01394 0.00628 -0.0162 1.0000 1.0000
-0.750 0.0110 0.01391 0.00627 -0.0132 1.0000 1.0000
-0.500 0.0092 0.01397 0.00635 -0.0091 1.0000 1.0000
-0.250 0.0047 0.01403 0.00641 -0.0045 1.0000 1.0000
0.000 0.0000 0.01405 0.00642 0.0000 1.0000 1.0000
0.250 -0.0046 0.01403 0.00640 0.0045 1.0000 1.0000
0.500 -0.0092 0.01397 0.00634 0.0091 1.0000 1.0000
0.750 -0.0110 0.01391 0.00627 0.0132 1.0000 1.0000
1.000 -0.0060 0.01393 0.00627 0.0162 1.0000 1.0000
1.250 0.0042 0.01405 0.00639 0.0184 1.0000 1.0000
1.500 0.0174 0.01423 0.00656 0.0201 1.0000 1.0000
1.750 0.0349 0.01447 0.00683 0.0209 0.9994 1.0000
2.000 0.0878 0.01500 0.00748 0.0149 0.9893 1.0000
2.250 0.1473 0.01543 0.00813 0.0079 0.9749 1.0000
2.500 0.2651 0.01541 0.00857 -0.0087 0.9451 1.0000
2.750 0.4416 0.01353 0.00752 -0.0314 0.8830 1.0000
3.000 0.4633 0.01302 0.00713 -0.0274 0.8231 1.0000
3.250 0.4707 0.01258 0.00661 -0.0208 0.7201 1.0000
3.500 0.4598 0.01450 0.00620 -0.0119 0.2622 1.0000
3.750 0.4647 0.01642 0.00728 -0.0079 0.1494 1.0000
4.000 0.4771 0.01759 0.00823 -0.0051 0.1149 1.0000
4.250 0.4922 0.01908 0.00953 -0.0027 0.0964 1.0000
4.500 0.5107 0.02032 0.01076 -0.0008 0.0804 1.0000
4.750 0.5322 0.02239 0.01272 0.0005 0.0705 1.0000
5.000 0.5543 0.02371 0.01435 0.0022 0.0635 1.0000
5.250 0.5751 0.02623 0.01684 0.0032 0.0574 1.0000
5.500 0.5962 0.02819 0.01927 0.0052 0.0557 1.0000
5.750 0.6160 0.03096 0.02242 0.0070 0.0562 1.0000
6.000 0.6333 0.03444 0.02628 0.0089 0.0569 1.0000
6.250 0.6497 0.03797 0.03074 0.0123 0.0650 1.0000
6.500 0.6643 0.04427 0.03755 0.0145 0.0829 1.0000
8.500 0.7048 0.08219 0.07735 0.0209 0.1110 1.0000
8.750 0.6887 0.08573 0.08102 0.0195 0.1108 1.0000
9.000 0.6645 0.08957 0.08488 0.0170 0.1103 1.0000
9.250 0.6472 0.09488 0.09015 0.0113 0.1100 1.0000
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Polar data table (+)
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