NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 50,000 Max Cl/Cd: 30.74 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf0115-il-50000.txt Download as CSV file: xf-nlf0115-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NLF(1)-0115
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3575 0.12529 0.11804 -0.0305 1.0000 0.2934
-10.750 -0.3585 0.12271 0.11554 -0.0299 1.0000 0.3061
-9.750 -0.3481 0.11241 0.10549 -0.0253 1.0000 0.3678
-9.500 -0.3387 0.10947 0.10260 -0.0239 1.0000 0.3848
-9.250 -0.3294 0.10673 0.09991 -0.0225 1.0000 0.4024
-9.000 -0.3215 0.10419 0.09742 -0.0208 1.0000 0.4219
-8.500 -0.3218 0.10012 0.09352 -0.0166 1.0000 0.4617
-7.750 -0.4609 0.08469 0.07874 -0.0232 1.0000 0.3083
-7.500 -0.5196 0.08110 0.07540 -0.0214 1.0000 0.2924
-7.250 -0.5677 0.07910 0.07358 -0.0170 1.0000 0.2923
-7.000 -0.6188 0.07631 0.07089 -0.0135 1.0000 0.2901
-6.750 -0.6736 0.07316 0.06770 -0.0107 1.0000 0.2872
-6.500 -0.7022 0.06426 0.05796 -0.0146 1.0000 0.2009
-6.250 -0.7090 0.05939 0.05198 -0.0134 1.0000 0.1585
-6.000 -0.6994 0.05565 0.04774 -0.0117 1.0000 0.1424
-5.750 -0.6879 0.05207 0.04385 -0.0102 1.0000 0.1337
-5.500 -0.6742 0.04955 0.04075 -0.0084 1.0000 0.1255
-5.250 -0.6591 0.04683 0.03769 -0.0069 1.0000 0.1211
-5.000 -0.6421 0.04451 0.03478 -0.0052 1.0000 0.1163
-4.750 -0.6241 0.04276 0.03253 -0.0036 1.0000 0.1150
-4.500 -0.6051 0.04086 0.03046 -0.0025 1.0000 0.1163
-4.250 -0.5851 0.03926 0.02866 -0.0013 1.0000 0.1176
-4.000 -0.5640 0.03780 0.02700 -0.0001 1.0000 0.1186
-3.750 -0.5419 0.03651 0.02554 0.0011 1.0000 0.1199
-3.500 -0.0995 0.04027 0.03188 -0.0317 1.0000 1.0000
-3.250 -0.0982 0.04027 0.03173 -0.0293 1.0000 1.0000
-3.000 -0.0961 0.04026 0.03159 -0.0270 1.0000 1.0000
-2.750 -0.0934 0.04026 0.03145 -0.0248 1.0000 1.0000
-2.500 -0.0901 0.04026 0.03132 -0.0226 1.0000 1.0000
-2.250 -0.0863 0.04026 0.03119 -0.0205 1.0000 1.0000
-2.000 -0.0822 0.04027 0.03108 -0.0183 1.0000 1.0000
-1.750 -0.0778 0.04029 0.03099 -0.0163 1.0000 1.0000
-1.500 -0.0732 0.04030 0.03091 -0.0142 1.0000 1.0000
-1.250 -0.0684 0.04033 0.03082 -0.0121 1.0000 1.0000
-1.000 -0.0635 0.04036 0.03077 -0.0101 1.0000 1.0000
-0.750 -0.0585 0.04039 0.03072 -0.0080 1.0000 1.0000
-0.500 -0.0536 0.04043 0.03068 -0.0059 1.0000 1.0000
-0.250 -0.0487 0.04047 0.03065 -0.0039 1.0000 1.0000
0.000 -0.0438 0.04051 0.03063 -0.0018 1.0000 1.0000
0.250 -0.0392 0.04055 0.03061 0.0003 1.0000 1.0000
0.500 -0.0348 0.04059 0.03059 0.0024 1.0000 1.0000
0.750 -0.0306 0.04062 0.03058 0.0045 1.0000 1.0000
1.000 -0.0268 0.04065 0.03057 0.0067 1.0000 1.0000
1.250 -0.0233 0.04067 0.03056 0.0089 1.0000 1.0000
1.500 -0.0204 0.04067 0.03053 0.0112 1.0000 1.0000
1.750 -0.0180 0.04065 0.03049 0.0135 1.0000 1.0000
2.000 -0.0162 0.04060 0.03043 0.0158 1.0000 1.0000
2.250 -0.0152 0.04053 0.03034 0.0182 1.0000 1.0000
2.500 -0.0149 0.04042 0.03023 0.0207 1.0000 1.0000
2.750 -0.0151 0.04028 0.03009 0.0232 1.0000 1.0000
3.000 -0.0151 0.04014 0.02995 0.0256 1.0000 1.0000
3.250 -0.0141 0.04008 0.02989 0.0277 1.0000 1.0000
3.500 -0.0097 0.04024 0.03003 0.0291 1.0000 1.0000
3.750 -0.0013 0.04070 0.03048 0.0296 1.0000 1.0000
4.000 0.0100 0.04140 0.03119 0.0296 1.0000 1.0000
4.250 0.2704 0.04854 0.03845 -0.0079 0.8393 1.0000
4.500 0.2829 0.04868 0.03862 -0.0064 0.8160 1.0000
4.750 0.3308 0.04920 0.03921 -0.0094 0.7905 1.0000
5.000 0.3546 0.04941 0.03947 -0.0092 0.7655 1.0000
5.250 0.3961 0.04954 0.03969 -0.0108 0.7405 1.0000
5.500 0.4377 0.04935 0.03960 -0.0120 0.7152 1.0000
5.750 0.4709 0.04913 0.03948 -0.0121 0.6892 1.0000
6.000 0.5324 0.04769 0.03823 -0.0142 0.6657 1.0000
6.250 0.5629 0.04691 0.03757 -0.0131 0.6381 1.0000
6.500 0.6437 0.04304 0.03399 -0.0150 0.6174 1.0000
6.750 0.6823 0.04072 0.03181 -0.0133 0.5891 1.0000
7.000 0.7464 0.03665 0.02796 -0.0132 0.5590 1.0000
7.250 0.8145 0.03249 0.02388 -0.0138 0.5171 1.0000
7.500 0.8810 0.02967 0.02073 -0.0155 0.4636 1.0000
7.750 0.9128 0.02989 0.02055 -0.0151 0.4212 1.0000
8.000 0.9482 0.03085 0.02114 -0.0160 0.3864 1.0000
8.250 0.9713 0.03222 0.02241 -0.0156 0.3612 1.0000
8.500 1.0037 0.03370 0.02368 -0.0166 0.3384 1.0000
8.750 1.0273 0.03531 0.02532 -0.0164 0.3209 1.0000
9.000 1.0514 0.03701 0.02702 -0.0164 0.3053 1.0000
9.250 1.0759 0.03879 0.02880 -0.0164 0.2911 1.0000
9.500 1.1002 0.04069 0.03073 -0.0164 0.2790 1.0000
9.750 1.1065 0.04276 0.03312 -0.0140 0.2700 1.0000
10.000 1.1269 0.04484 0.03525 -0.0136 0.2597 1.0000
10.250 1.1333 0.04711 0.03778 -0.0114 0.2521 1.0000
10.500 1.1480 0.04959 0.04037 -0.0105 0.2446 1.0000
10.750 1.1380 0.05226 0.04338 -0.0066 0.2395 1.0000
11.000 1.1648 0.05464 0.04572 -0.0071 0.2306 1.0000
11.250 1.1414 0.05784 0.04930 -0.0023 0.2284 1.0000
11.500 1.1133 0.06130 0.05304 0.0024 0.2270 1.0000
11.750 1.0777 0.06537 0.05732 0.0069 0.2266 1.0000
12.000 1.0295 0.07097 0.06309 0.0100 0.2276 1.0000
12.250 0.9720 0.07892 0.07113 0.0106 0.2297 1.0000
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Polar data table (+)
Polar graphs
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