NPL 9615 AIRFOIL (npl9615-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9615 AIRFOIL (npl9615-il) Reynolds number: 50,000 Max Cl/Cd: 30.53 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9615-il-50000-n5.txt Download as CSV file: xf-npl9615-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9615 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6144 0.08365 0.07586 -0.0328 1.0000 0.0516
-9.500 -0.6274 0.07922 0.07140 -0.0341 1.0000 0.0513
-9.250 -0.6424 0.07528 0.06740 -0.0338 1.0000 0.0511
-9.000 -0.6554 0.07137 0.06337 -0.0331 1.0000 0.0509
-8.750 -0.6657 0.06752 0.05934 -0.0319 1.0000 0.0509
-8.500 -0.6735 0.06375 0.05534 -0.0304 1.0000 0.0511
-8.250 -0.6790 0.06007 0.05135 -0.0284 1.0000 0.0514
-8.000 -0.6796 0.05673 0.04773 -0.0263 1.0000 0.0520
-7.750 -0.6716 0.05424 0.04511 -0.0247 1.0000 0.0531
-7.500 -0.6657 0.05146 0.04208 -0.0226 1.0000 0.0542
-7.250 -0.6591 0.04859 0.03888 -0.0203 1.0000 0.0552
-7.000 -0.6512 0.04571 0.03559 -0.0179 1.0000 0.0562
-6.750 -0.6414 0.04284 0.03221 -0.0153 1.0000 0.0573
-6.500 -0.6266 0.04059 0.02976 -0.0136 1.0000 0.0590
-6.250 -0.6108 0.03863 0.02754 -0.0118 1.0000 0.0619
-6.000 -0.5944 0.03676 0.02540 -0.0101 1.0000 0.0658
-5.750 -0.5764 0.03506 0.02340 -0.0084 1.0000 0.0701
-5.500 -0.5562 0.03340 0.02161 -0.0072 1.0000 0.0738
-5.250 -0.5361 0.03202 0.01991 -0.0057 1.0000 0.0792
-5.000 -0.5149 0.03076 0.01869 -0.0048 1.0000 0.0850
-4.750 -0.4916 0.02946 0.01726 -0.0038 1.0000 0.0895
-4.500 -0.4683 0.02837 0.01614 -0.0028 1.0000 0.0944
-4.250 -0.4443 0.02734 0.01503 -0.0018 1.0000 0.0984
-4.000 -0.4221 0.02643 0.01413 -0.0007 1.0000 0.1028
-3.500 -0.3812 0.02488 0.01252 0.0021 1.0000 0.1120
-3.250 -0.3622 0.02423 0.01179 0.0036 1.0000 0.1170
-3.000 -0.3440 0.02356 0.01112 0.0050 1.0000 0.1240
-2.750 -0.3254 0.02297 0.01051 0.0064 1.0000 0.1333
-2.500 -0.3072 0.02233 0.00992 0.0077 1.0000 0.1462
-2.250 -0.2901 0.02145 0.00936 0.0090 1.0000 0.1805
-2.000 -0.2852 0.01901 0.00937 0.0131 1.0000 0.6036
-1.750 -0.2552 0.01902 0.01009 0.0157 1.0000 0.8032
-1.500 -0.1905 0.01981 0.01079 0.0114 1.0000 0.9225
-1.250 -0.0483 0.02049 0.01099 -0.0085 1.0000 0.9887
-1.000 -0.0154 0.02037 0.01073 -0.0112 1.0000 1.0000
-0.750 -0.0104 0.02036 0.01066 -0.0089 0.9963 1.0000
-0.500 0.0355 0.02033 0.01050 -0.0137 0.9791 1.0000
-0.250 0.0805 0.02029 0.01035 -0.0181 0.9624 1.0000
0.000 0.1260 0.02023 0.01021 -0.0223 0.9461 1.0000
0.250 0.1713 0.02015 0.01008 -0.0263 0.9294 1.0000
0.500 0.2131 0.02005 0.00994 -0.0294 0.9112 1.0000
0.750 0.2523 0.01995 0.00982 -0.0318 0.8927 1.0000
1.000 0.2891 0.01986 0.00971 -0.0336 0.8737 1.0000
1.250 0.3220 0.01979 0.00964 -0.0346 0.8531 1.0000
1.500 0.3468 0.01979 0.00963 -0.0339 0.8278 1.0000
1.750 0.3761 0.01968 0.00950 -0.0337 0.8053 1.0000
2.000 0.4047 0.01960 0.00939 -0.0333 0.7836 1.0000
2.250 0.4301 0.01962 0.00937 -0.0323 0.7604 1.0000
2.500 0.4545 0.01967 0.00937 -0.0311 0.7362 1.0000
2.750 0.4760 0.01978 0.00945 -0.0295 0.7103 1.0000
3.000 0.4979 0.01988 0.00951 -0.0278 0.6841 1.0000
3.250 0.5192 0.02001 0.00958 -0.0260 0.6580 1.0000
3.500 0.5396 0.02018 0.00972 -0.0242 0.6311 1.0000
3.750 0.5610 0.02037 0.00984 -0.0225 0.6049 1.0000
4.000 0.5814 0.02060 0.01005 -0.0207 0.5772 1.0000
4.250 0.6018 0.02086 0.01026 -0.0190 0.5490 1.0000
4.500 0.6214 0.02115 0.01050 -0.0171 0.5189 1.0000
4.750 0.6403 0.02148 0.01078 -0.0152 0.4873 1.0000
5.000 0.6590 0.02186 0.01108 -0.0133 0.4554 1.0000
5.250 0.6774 0.02230 0.01145 -0.0114 0.4238 1.0000
5.500 0.6954 0.02280 0.01189 -0.0095 0.3919 1.0000
5.750 0.7134 0.02337 0.01240 -0.0077 0.3614 1.0000
6.000 0.7314 0.02402 0.01293 -0.0059 0.3345 1.0000
6.250 0.7496 0.02473 0.01361 -0.0043 0.3088 1.0000
6.500 0.7677 0.02550 0.01432 -0.0027 0.2868 1.0000
6.750 0.7858 0.02633 0.01508 -0.0012 0.2665 1.0000
7.000 0.8037 0.02720 0.01592 0.0004 0.2478 1.0000
7.250 0.8217 0.02814 0.01688 0.0018 0.2305 1.0000
7.500 0.8393 0.02909 0.01786 0.0033 0.2137 1.0000
7.750 0.8557 0.03006 0.01884 0.0049 0.1975 1.0000
8.000 0.8709 0.03105 0.01982 0.0066 0.1814 1.0000
8.250 0.8850 0.03209 0.02089 0.0084 0.1655 1.0000
8.500 0.8982 0.03320 0.02208 0.0102 0.1496 1.0000
8.750 0.9105 0.03435 0.02321 0.0120 0.1360 1.0000
9.000 0.9223 0.03566 0.02463 0.0138 0.1221 1.0000
9.250 0.9333 0.03697 0.02591 0.0156 0.1112 1.0000
9.500 0.9443 0.03850 0.02761 0.0174 0.1007 1.0000
9.750 0.9551 0.04003 0.02915 0.0191 0.0931 1.0000
10.000 0.9657 0.04185 0.03117 0.0209 0.0859 1.0000
10.250 0.9764 0.04342 0.03272 0.0224 0.0813 1.0000
10.500 0.9845 0.04550 0.03505 0.0242 0.0763 1.0000
10.750 0.9917 0.04732 0.03699 0.0259 0.0728 1.0000
11.000 0.9967 0.04963 0.03951 0.0277 0.0700 1.0000
11.250 1.0020 0.05189 0.04189 0.0292 0.0677 1.0000
11.500 1.0001 0.05480 0.04509 0.0308 0.0657 1.0000
11.750 0.9962 0.05778 0.04829 0.0320 0.0640 1.0000
12.000 0.9975 0.06025 0.05081 0.0329 0.0624 1.0000
12.250 0.9807 0.06472 0.05564 0.0330 0.0616 1.0000
12.500 0.9615 0.06981 0.06102 0.0319 0.0610 1.0000
12.750 0.9381 0.07600 0.06746 0.0294 0.0609 1.0000
13.000 0.9084 0.08393 0.07562 0.0251 0.0611 1.0000
13.250 0.8739 0.09390 0.08576 0.0191 0.0617 1.0000
13.500 0.8377 0.10574 0.09771 0.0118 0.0624 1.0000
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Polar data table (+)
Polar graphs
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