LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 50,000 Max Cl/Cd: 33.99 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lds2-il-50000.txt Download as CSV file: xf-lds2-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: LDS-2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3788 0.11221 0.10490 -0.0185 1.0000 0.3004
-9.500 -0.3817 0.10971 0.10248 -0.0185 1.0000 0.3119
-9.250 -0.3993 0.10924 0.10212 -0.0184 1.0000 0.3248
-9.000 -0.3803 0.10500 0.09789 -0.0174 1.0000 0.3397
-8.750 -0.2916 0.09527 0.08883 -0.0208 1.0000 0.3567
-8.500 -0.2661 0.09037 0.08391 -0.0204 1.0000 0.3652
-8.250 -0.2724 0.08762 0.08126 -0.0194 1.0000 0.3752
-8.000 -0.2884 0.08610 0.07987 -0.0177 1.0000 0.3881
-7.750 -0.2721 0.08151 0.07529 -0.0173 1.0000 0.3918
-7.500 -0.3452 0.08660 0.07985 -0.0123 1.0000 0.4109
-6.750 -0.5582 0.06345 0.05700 -0.0316 1.0000 0.1800
-6.500 -0.5694 0.05833 0.05160 -0.0308 1.0000 0.1620
-6.250 -0.5773 0.05366 0.04642 -0.0295 1.0000 0.1484
-6.000 -0.5757 0.04992 0.04234 -0.0277 1.0000 0.1423
-5.750 -0.5725 0.04673 0.03835 -0.0257 1.0000 0.1357
-5.500 -0.5618 0.04391 0.03526 -0.0240 1.0000 0.1346
-5.250 -0.5492 0.04127 0.03229 -0.0224 1.0000 0.1333
-5.000 -0.5342 0.03886 0.02952 -0.0208 1.0000 0.1316
-4.750 -0.5171 0.03661 0.02688 -0.0193 1.0000 0.1307
-4.500 -0.4986 0.03480 0.02466 -0.0179 1.0000 0.1323
-4.250 -0.4792 0.03334 0.02276 -0.0165 1.0000 0.1355
-4.000 -0.4586 0.03171 0.02094 -0.0153 1.0000 0.1389
-3.750 -0.4373 0.03032 0.01949 -0.0142 1.0000 0.1433
-3.500 -0.4162 0.02931 0.01828 -0.0129 1.0000 0.1512
-3.250 -0.3956 0.02816 0.01724 -0.0117 1.0000 0.1613
-3.000 -0.3746 0.02716 0.01628 -0.0104 1.0000 0.1755
-2.750 -0.3531 0.02618 0.01537 -0.0094 1.0000 0.2000
-2.500 -0.3336 0.02464 0.01445 -0.0084 1.0000 0.2628
-2.250 -0.3374 0.02257 0.01498 0.0004 1.0000 0.6993
-2.000 -0.1313 0.02606 0.01804 -0.0205 1.0000 1.0000
-1.750 -0.1576 0.02504 0.01702 -0.0157 1.0000 1.0000
-1.500 -0.1792 0.02409 0.01598 -0.0110 1.0000 1.0000
-1.250 -0.1802 0.02377 0.01540 -0.0086 1.0000 1.0000
-1.000 -0.1712 0.02382 0.01517 -0.0071 1.0000 1.0000
-0.750 -0.1584 0.02403 0.01510 -0.0061 1.0000 1.0000
-0.500 -0.1438 0.02434 0.01517 -0.0052 1.0000 1.0000
-0.250 -0.1282 0.02471 0.01532 -0.0044 1.0000 1.0000
0.000 -0.1120 0.02514 0.01555 -0.0038 1.0000 1.0000
0.250 -0.0955 0.02561 0.01583 -0.0032 1.0000 1.0000
0.500 -0.0787 0.02613 0.01619 -0.0026 1.0000 1.0000
0.750 -0.0456 0.02717 0.01705 -0.0052 0.9941 1.0000
1.000 -0.0077 0.02834 0.01806 -0.0087 0.9850 1.0000
1.250 0.0255 0.02935 0.01896 -0.0113 0.9761 1.0000
1.500 0.0576 0.03038 0.01989 -0.0137 0.9667 1.0000
1.750 0.0910 0.03150 0.02092 -0.0162 0.9570 1.0000
2.000 0.1297 0.03281 0.02215 -0.0196 0.9461 1.0000
2.250 0.1613 0.03380 0.02311 -0.0217 0.9331 1.0000
2.500 0.1966 0.03487 0.02416 -0.0242 0.9180 1.0000
2.750 0.2313 0.03593 0.02521 -0.0265 0.9024 1.0000
3.000 0.2641 0.03698 0.02626 -0.0284 0.8871 1.0000
3.250 0.2975 0.03801 0.02732 -0.0303 0.8712 1.0000
3.500 0.3323 0.03901 0.02837 -0.0322 0.8543 1.0000
3.750 0.3729 0.03995 0.02938 -0.0347 0.8359 1.0000
4.000 0.4087 0.04073 0.03023 -0.0362 0.8159 1.0000
4.250 0.4382 0.04135 0.03095 -0.0365 0.7938 1.0000
4.500 0.4929 0.04149 0.03124 -0.0395 0.7707 1.0000
4.750 0.5216 0.04177 0.03164 -0.0390 0.7462 1.0000
5.000 0.5868 0.04076 0.03089 -0.0418 0.7223 1.0000
5.250 0.6202 0.04031 0.03060 -0.0409 0.6955 1.0000
5.500 0.6915 0.03753 0.02815 -0.0423 0.6689 1.0000
5.750 0.7733 0.03305 0.02401 -0.0432 0.6415 1.0000
6.000 0.8111 0.03079 0.02191 -0.0404 0.6046 1.0000
6.250 0.8544 0.02799 0.01918 -0.0377 0.5555 1.0000
6.500 0.8819 0.02643 0.01735 -0.0337 0.4891 1.0000
6.750 0.9000 0.02648 0.01679 -0.0299 0.4197 1.0000
7.000 0.9155 0.02765 0.01742 -0.0271 0.3643 1.0000
7.250 0.9345 0.02914 0.01854 -0.0253 0.3237 1.0000
7.500 0.9574 0.03085 0.01999 -0.0243 0.2921 1.0000
7.750 0.9848 0.03265 0.02151 -0.0240 0.2676 1.0000
8.000 1.0066 0.03446 0.02337 -0.0231 0.2490 1.0000
8.250 1.0305 0.03641 0.02533 -0.0225 0.2342 1.0000
8.500 1.0544 0.03840 0.02726 -0.0220 0.2208 1.0000
8.750 1.0677 0.04052 0.02979 -0.0200 0.2114 1.0000
9.000 1.0875 0.04293 0.03232 -0.0191 0.2030 1.0000
9.250 1.1000 0.04521 0.03489 -0.0173 0.1950 1.0000
9.500 1.1170 0.04798 0.03777 -0.0163 0.1889 1.0000
9.750 1.1165 0.05102 0.04131 -0.0133 0.1853 1.0000
10.000 1.1189 0.05398 0.04460 -0.0109 0.1811 1.0000
10.250 1.1407 0.05689 0.04742 -0.0106 0.1749 1.0000
10.500 1.1273 0.06049 0.05149 -0.0072 0.1736 1.0000
10.750 1.1108 0.06447 0.05584 -0.0040 0.1731 1.0000
11.000 1.0877 0.06871 0.06036 -0.0008 0.1732 1.0000
11.250 1.0601 0.07301 0.06482 0.0022 0.1738 1.0000
11.500 1.0319 0.07801 0.06996 0.0039 0.1746 1.0000
11.750 1.0068 0.08379 0.07583 0.0041 0.1754 1.0000
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Polar data table (+)
Polar graphs
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