NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Reynolds number: 100,000 Max Cl/Cd: 35.88 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf414f-il-100000.txt Download as CSV file: xf-nlf414f-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF 0414F AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5018 0.12201 0.11754 -0.0304 1.0000 0.1042
-9.750 -0.5057 0.11936 0.11492 -0.0297 1.0000 0.1077
-9.500 -0.5215 0.11617 0.11178 -0.0305 1.0000 0.1112
-9.250 -0.5548 0.11233 0.10802 -0.0334 1.0000 0.1130
-9.000 -0.5891 0.10812 0.10387 -0.0356 1.0000 0.1134
-8.750 -0.6222 0.10505 0.10081 -0.0347 1.0000 0.1135
-8.500 -0.5616 0.10292 0.09870 -0.0286 1.0000 0.1210
-8.250 -0.5802 0.09947 0.09529 -0.0285 1.0000 0.1236
-8.000 -0.6111 0.09583 0.09169 -0.0281 1.0000 0.1246
-7.750 -0.6432 0.09235 0.08821 -0.0272 1.0000 0.1253
-7.500 -0.6780 0.08830 0.08403 -0.0279 1.0000 0.1278
-7.250 -0.5858 0.08284 0.07905 -0.0243 1.0000 0.1424
-7.000 -0.6876 0.08066 0.07636 -0.0255 1.0000 0.1350
-6.750 -0.6905 0.07763 0.07324 -0.0247 1.0000 0.1415
-6.500 -0.6986 0.07325 0.06867 -0.0249 1.0000 0.1491
-6.250 -0.6898 0.07066 0.06609 -0.0233 1.0000 0.1556
-6.000 -0.6879 0.06698 0.06226 -0.0233 1.0000 0.1669
-5.750 -0.6822 0.06391 0.05901 -0.0232 1.0000 0.1818
-5.500 -0.6727 0.06116 0.05618 -0.0227 1.0000 0.1981
-5.250 -0.6614 0.05849 0.05350 -0.0218 1.0000 0.2156
-5.000 -0.6489 0.05604 0.05109 -0.0206 1.0000 0.2348
-4.750 -0.5814 0.04312 0.03538 -0.0261 1.0000 0.0819
-4.500 -0.5535 0.03964 0.03120 -0.0254 1.0000 0.0693
-4.250 -0.5289 0.03711 0.02839 -0.0252 1.0000 0.0661
-4.000 -0.5037 0.03530 0.02622 -0.0248 1.0000 0.0650
-3.750 -0.4792 0.03400 0.02467 -0.0244 1.0000 0.0661
-3.500 -0.4544 0.03281 0.02326 -0.0239 1.0000 0.0669
-3.250 -0.4295 0.03170 0.02199 -0.0233 1.0000 0.0672
-3.000 -0.4047 0.03080 0.02097 -0.0228 1.0000 0.0684
-2.750 -0.3801 0.03012 0.02019 -0.0222 1.0000 0.0704
-2.500 -0.3548 0.02921 0.01941 -0.0222 1.0000 0.0749
-2.250 -0.3298 0.02881 0.01905 -0.0222 1.0000 0.0834
-2.000 -0.3021 0.02820 0.01854 -0.0228 1.0000 0.0963
-1.750 -0.2704 0.02599 0.01967 -0.0231 1.0000 0.6202
-1.500 -0.2801 0.02799 0.02165 -0.0114 1.0000 0.8122
-1.250 -0.2868 0.02829 0.02195 -0.0018 1.0000 0.8552
-1.000 -0.1484 0.03178 0.02509 -0.0135 1.0000 1.0000
-0.750 -0.1410 0.03166 0.02486 -0.0113 1.0000 1.0000
-0.500 -0.1336 0.03156 0.02466 -0.0090 1.0000 1.0000
-0.250 -0.1261 0.03148 0.02449 -0.0068 1.0000 1.0000
0.000 -0.1186 0.03141 0.02435 -0.0046 1.0000 1.0000
0.250 -0.1111 0.03136 0.02423 -0.0024 1.0000 1.0000
0.500 -0.1036 0.03133 0.02413 -0.0002 1.0000 1.0000
0.750 -0.0959 0.03131 0.02406 0.0019 1.0000 1.0000
1.000 -0.0879 0.03132 0.02402 0.0039 1.0000 1.0000
1.250 -0.0798 0.03136 0.02401 0.0058 1.0000 1.0000
1.500 -0.0643 0.03167 0.02428 0.0063 0.9984 1.0000
1.750 -0.0235 0.03302 0.02556 0.0019 0.9879 1.0000
2.000 0.0149 0.03432 0.02680 -0.0019 0.9757 1.0000
2.250 0.0504 0.03551 0.02795 -0.0050 0.9623 1.0000
2.500 0.0835 0.03662 0.02904 -0.0076 0.9484 1.0000
2.750 0.1152 0.03770 0.03010 -0.0098 0.9344 1.0000
3.000 0.1460 0.03876 0.03117 -0.0118 0.9203 1.0000
3.250 0.1774 0.03984 0.03225 -0.0138 0.9056 1.0000
3.500 0.2103 0.04092 0.03335 -0.0159 0.8899 1.0000
3.750 0.2486 0.04207 0.03452 -0.0186 0.8727 1.0000
4.000 0.3166 0.04223 0.03470 -0.0232 0.8275 1.0000
4.250 0.3646 0.04271 0.03522 -0.0262 0.8101 1.0000
4.500 0.3967 0.04291 0.03548 -0.0271 0.7950 1.0000
4.750 0.4245 0.04306 0.03572 -0.0275 0.7806 1.0000
5.000 0.4546 0.04314 0.03588 -0.0282 0.7664 1.0000
5.250 0.5005 0.04242 0.03525 -0.0299 0.7504 1.0000
5.500 0.5529 0.04096 0.03392 -0.0318 0.7351 1.0000
5.750 0.5920 0.03992 0.03301 -0.0326 0.7218 1.0000
6.000 0.6301 0.03873 0.03196 -0.0332 0.7089 1.0000
6.250 0.6721 0.03688 0.03030 -0.0335 0.6952 1.0000
6.500 0.7185 0.03414 0.02774 -0.0336 0.6800 1.0000
6.750 0.7447 0.03250 0.02628 -0.0320 0.6578 1.0000
7.000 0.7840 0.02973 0.02371 -0.0310 0.6362 1.0000
7.250 0.8082 0.02823 0.02236 -0.0291 0.5974 1.0000
7.500 0.8590 0.02394 0.01653 -0.0252 0.3456 1.0000
7.750 0.8521 0.02634 0.01775 -0.0213 0.2158 1.0000
8.000 0.8595 0.02818 0.01900 -0.0192 0.1662 1.0000
8.250 0.8760 0.02953 0.02014 -0.0181 0.1397 1.0000
8.500 0.8981 0.03074 0.02118 -0.0176 0.1236 1.0000
8.750 0.9259 0.03185 0.02222 -0.0176 0.1117 1.0000
9.000 0.9592 0.03306 0.02336 -0.0182 0.1025 1.0000
9.250 0.9959 0.03432 0.02459 -0.0193 0.0957 1.0000
9.500 1.0400 0.03611 0.02644 -0.0211 0.0898 1.0000
9.750 1.0732 0.03771 0.02822 -0.0220 0.0851 1.0000
10.000 1.1143 0.03994 0.03051 -0.0241 0.0818 1.0000
10.250 1.1548 0.04347 0.03423 -0.0263 0.0794 1.0000
10.500 1.1706 0.04557 0.03678 -0.0252 0.0777 1.0000
10.750 1.1853 0.04809 0.03971 -0.0241 0.0762 1.0000
11.000 1.1984 0.05120 0.04322 -0.0230 0.0756 1.0000
11.250 1.2058 0.05459 0.04702 -0.0214 0.0755 1.0000
11.500 1.2069 0.05816 0.05097 -0.0193 0.0759 1.0000
11.750 1.2029 0.06187 0.05503 -0.0170 0.0764 1.0000
12.000 1.1946 0.06566 0.05915 -0.0146 0.0768 1.0000
12.250 1.1827 0.06959 0.06337 -0.0123 0.0773 1.0000
12.500 1.1682 0.07373 0.06776 -0.0102 0.0777 1.0000
12.750 1.1519 0.07813 0.07239 -0.0085 0.0782 1.0000
13.000 1.1362 0.08293 0.07738 -0.0073 0.0788 1.0000
13.250 1.1288 0.08853 0.08311 -0.0069 0.0796 1.0000
13.500 0.8934 0.12369 0.11924 -0.0228 0.1099 1.0000
13.750 0.9738 0.11072 0.10618 -0.0116 0.0946 1.0000
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Polar data table (+)
Polar graphs
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