NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Reynolds number: 50,000 Max Cl/Cd: 23.37 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf415-il-50000.txt Download as CSV file: xf-nlf415-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF(2)-0415 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5972 0.10246 0.09657 -0.0068 1.0000 0.3382
-7.250 -0.6619 0.09464 0.08899 -0.0094 1.0000 0.3053
-7.000 -0.7220 0.08746 0.08196 -0.0106 1.0000 0.2913
-6.750 -0.7794 0.07838 0.07283 -0.0149 1.0000 0.2758
-6.500 -0.8093 0.06847 0.06223 -0.0215 1.0000 0.2314
-6.250 -0.7958 0.06170 0.05391 -0.0256 1.0000 0.1681
-6.000 -0.7730 0.05746 0.04923 -0.0252 1.0000 0.1473
-5.750 -0.7518 0.05414 0.04520 -0.0247 1.0000 0.1344
-5.500 -0.7284 0.05131 0.04151 -0.0240 1.0000 0.1235
-5.250 -0.7062 0.04833 0.03832 -0.0232 1.0000 0.1193
-5.000 -0.6822 0.04559 0.03520 -0.0222 1.0000 0.1136
-4.750 -0.6561 0.04432 0.03317 -0.0209 1.0000 0.1083
-4.500 -0.6325 0.04216 0.03082 -0.0197 1.0000 0.1069
-4.250 -0.6087 0.04043 0.02894 -0.0182 1.0000 0.1061
-4.000 -0.5851 0.03921 0.02759 -0.0164 1.0000 0.1067
-3.750 -0.5631 0.03823 0.02663 -0.0138 1.0000 0.1098
-3.500 -0.1790 0.05118 0.04173 -0.0293 1.0000 1.0000
-3.250 -0.1697 0.05064 0.04098 -0.0277 1.0000 1.0000
-3.000 -0.1604 0.05013 0.04027 -0.0261 1.0000 1.0000
-2.750 -0.1510 0.04964 0.03962 -0.0245 1.0000 1.0000
-2.500 -0.1497 0.04908 0.03895 -0.0211 1.0000 0.9977
-2.250 -0.1532 0.04861 0.03839 -0.0168 1.0000 0.9941
-2.000 -0.1523 0.04804 0.03774 -0.0133 1.0000 0.9912
-1.750 -0.1525 0.04754 0.03717 -0.0097 1.0000 0.9883
-1.500 -0.1536 0.04708 0.03661 -0.0059 1.0000 0.9857
-1.250 -0.1547 0.04660 0.03606 -0.0021 1.0000 0.9831
-1.000 -0.1502 0.04610 0.03549 0.0005 1.0000 0.9815
-0.750 -0.1473 0.04560 0.03493 0.0035 1.0000 0.9796
-0.500 -0.1454 0.04512 0.03439 0.0066 1.0000 0.9777
-0.250 -0.1420 0.04467 0.03388 0.0095 1.0000 0.9766
0.000 -0.1402 0.04420 0.03336 0.0127 1.0000 0.9753
0.250 -0.1390 0.04373 0.03284 0.0159 1.0000 0.9742
0.500 -0.1335 0.04331 0.03239 0.0183 1.0000 0.9739
0.750 -0.1280 0.04290 0.03195 0.0207 1.0000 0.9738
1.000 -0.1242 0.04246 0.03148 0.0234 1.0000 0.9733
1.250 -0.1165 0.04209 0.03109 0.0253 1.0000 0.9736
1.500 -0.1045 0.04183 0.03081 0.0264 1.0000 0.9745
1.750 -0.0919 0.04161 0.03057 0.0273 1.0000 0.9757
2.000 -0.0806 0.04138 0.03034 0.0284 1.0000 0.9766
2.250 -0.0681 0.04120 0.03017 0.0293 1.0000 0.9779
2.500 -0.0542 0.04110 0.03008 0.0299 1.0000 0.9796
2.750 -0.0384 0.04109 0.03009 0.0300 1.0000 0.9821
3.000 -0.0204 0.04116 0.03021 0.0297 1.0000 0.9849
3.250 0.0003 0.04132 0.03041 0.0288 1.0000 0.9878
3.500 0.0192 0.04147 0.03062 0.0282 1.0000 0.9910
3.750 0.0370 0.04164 0.03087 0.0277 1.0000 0.9948
4.000 0.0543 0.04193 0.03124 0.0273 1.0000 1.0000
4.250 0.0569 0.04158 0.03096 0.0296 1.0000 1.0000
4.500 0.0594 0.04122 0.03069 0.0319 1.0000 1.0000
4.750 0.0626 0.04091 0.03045 0.0339 1.0000 1.0000
5.000 0.0694 0.04080 0.03043 0.0352 1.0000 1.0000
5.250 0.0813 0.04102 0.03076 0.0354 1.0000 1.0000
5.500 0.0970 0.04153 0.03138 0.0348 1.0000 1.0000
5.750 0.1152 0.04227 0.03224 0.0336 1.0000 1.0000
6.000 0.1349 0.04320 0.03330 0.0321 1.0000 1.0000
6.250 0.1552 0.04430 0.03457 0.0303 1.0000 1.0000
6.500 0.1757 0.04556 0.03599 0.0283 1.0000 1.0000
6.750 0.1960 0.04698 0.03758 0.0262 1.0000 1.0000
7.000 0.2298 0.04960 0.04043 0.0212 0.9932 1.0000
7.250 0.4468 0.05206 0.04390 -0.0053 0.8102 1.0000
7.750 0.6663 0.03148 0.02258 -0.0016 0.3383 1.0000
8.000 0.7109 0.03343 0.02356 -0.0034 0.2527 1.0000
8.250 0.8863 0.03793 0.02783 -0.0240 0.1783 1.0000
8.500 0.9624 0.04259 0.03257 -0.0326 0.1564 1.0000
8.750 0.9803 0.04492 0.03553 -0.0313 0.1480 1.0000
9.000 1.0087 0.04864 0.03955 -0.0322 0.1389 1.0000
9.250 1.0226 0.05161 0.04298 -0.0308 0.1316 1.0000
9.500 1.0418 0.05590 0.04753 -0.0307 0.1257 1.0000
9.750 1.0400 0.05925 0.05147 -0.0273 0.1235 1.0000
10.000 1.0373 0.06277 0.05548 -0.0242 0.1215 1.0000
10.250 1.0310 0.06659 0.05969 -0.0211 0.1207 1.0000
10.500 1.0193 0.07057 0.06400 -0.0176 0.1218 1.0000
10.750 1.0053 0.07465 0.06834 -0.0143 0.1233 1.0000
11.000 0.9928 0.07904 0.07293 -0.0118 0.1248 1.0000
11.250 0.9818 0.08383 0.07785 -0.0100 0.1261 1.0000
11.500 0.9785 0.08941 0.08353 -0.0093 0.1271 1.0000
11.750 0.8959 0.09403 0.08849 -0.0060 0.1386 1.0000
12.000 0.8387 0.10266 0.09724 -0.0090 0.1508 1.0000
12.250 0.8462 0.11255 0.10719 -0.0121 0.1712 1.0000
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Polar data table (+)
Polar graphs
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