NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA NLF1015 (nlf1015-il) Reynolds number: 100,000 Max Cl/Cd: 38.64 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf1015-il-100000-n5.txt Download as CSV file: xf-nlf1015-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA NLF1015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1834 0.10145 0.09623 -0.1053 0.9376 0.0312
-10.250 -0.1994 0.09210 0.08691 -0.1110 0.9308 0.0286
-10.000 -0.1967 0.08710 0.08192 -0.1143 0.9266 0.0284
-9.750 -0.1924 0.08147 0.07628 -0.1189 0.9238 0.0281
-9.500 -0.1979 0.07620 0.07102 -0.1217 0.9172 0.0277
-9.250 -0.2110 0.06778 0.06254 -0.1291 0.9113 0.0275
-9.000 -0.2280 0.06254 0.05721 -0.1326 0.9035 0.0270
-8.750 -0.2473 0.05809 0.05260 -0.1349 0.8958 0.0267
-8.500 -0.2700 0.05531 0.04969 -0.1334 0.8856 0.0266
-8.250 -0.2750 0.05111 0.04516 -0.1351 0.8806 0.0266
-8.000 -0.2888 0.04899 0.04281 -0.1320 0.8719 0.0267
-7.750 -0.2841 0.04545 0.03885 -0.1325 0.8674 0.0272
-7.250 -0.2746 0.04051 0.03307 -0.1299 0.8565 0.0281
-7.000 -0.2557 0.03795 0.03008 -0.1303 0.8536 0.0282
-6.750 -0.2307 0.03555 0.02726 -0.1313 0.8518 0.0283
-6.500 -0.2017 0.03344 0.02473 -0.1325 0.8505 0.0286
-6.250 -0.2007 0.03290 0.02401 -0.1284 0.8430 0.0288
-6.000 -0.1771 0.03135 0.02231 -0.1284 0.8402 0.0293
-5.750 -0.1500 0.03003 0.02086 -0.1289 0.8384 0.0300
-5.500 -0.1211 0.02890 0.01964 -0.1297 0.8370 0.0310
-5.250 -0.0906 0.02791 0.01854 -0.1306 0.8358 0.0323
-5.000 -0.0897 0.02807 0.01864 -0.1265 0.8287 0.0337
-4.750 -0.0653 0.02755 0.01797 -0.1264 0.8258 0.0365
-4.500 -0.0366 0.02667 0.01708 -0.1272 0.8239 0.0391
-4.250 -0.0054 0.02596 0.01627 -0.1284 0.8225 0.0425
-4.000 0.0274 0.02528 0.01548 -0.1299 0.8213 0.0482
-3.750 0.0348 0.02551 0.01571 -0.1271 0.8154 0.0559
-3.500 0.0597 0.02498 0.01542 -0.1275 0.8122 0.0965
-3.250 0.0920 0.02402 0.01508 -0.1299 0.8103 0.2272
-3.000 0.1241 0.02289 0.01526 -0.1320 0.8091 0.4876
-2.750 0.1494 0.02320 0.01578 -0.1308 0.8075 0.6062
-2.500 0.1784 0.02345 0.01590 -0.1305 0.8062 0.6433
-2.250 0.1778 0.02461 0.01703 -0.1261 0.7983 0.6604
-2.000 0.2020 0.02497 0.01725 -0.1254 0.7957 0.6821
-1.750 0.2265 0.02524 0.01742 -0.1245 0.7937 0.6991
-1.500 0.2539 0.02537 0.01745 -0.1241 0.7922 0.7144
-1.250 0.2582 0.02635 0.01841 -0.1204 0.7858 0.7254
-1.000 0.2744 0.02685 0.01885 -0.1184 0.7819 0.7368
-0.750 0.2992 0.02702 0.01894 -0.1177 0.7797 0.7489
-0.500 0.3282 0.02709 0.01891 -0.1179 0.7780 0.7604
-0.250 0.3557 0.02708 0.01882 -0.1176 0.7766 0.7686
0.000 0.3549 0.02836 0.02010 -0.1140 0.7680 0.7765
0.250 0.3794 0.02850 0.02020 -0.1135 0.7654 0.7830
0.500 0.4123 0.02853 0.02012 -0.1148 0.7637 0.7900
0.750 0.4418 0.02844 0.01999 -0.1151 0.7622 0.7946
1.250 0.4726 0.02981 0.02133 -0.1126 0.7508 0.8058
1.500 0.5023 0.02978 0.02126 -0.1131 0.7489 0.8099
1.750 0.5355 0.02966 0.02112 -0.1142 0.7474 0.8145
2.250 0.5671 0.03098 0.02246 -0.1118 0.7355 0.8244
2.500 0.5998 0.03087 0.02234 -0.1128 0.7336 0.8291
2.750 0.6358 0.03069 0.02215 -0.1143 0.7322 0.8342
3.250 0.6671 0.03188 0.02343 -0.1116 0.7194 0.8444
3.500 0.7030 0.03163 0.02319 -0.1131 0.7178 0.8500
4.000 0.7363 0.03264 0.02433 -0.1106 0.7048 0.8622
4.250 0.7708 0.03224 0.02398 -0.1115 0.7030 0.8677
4.750 0.8059 0.03301 0.02491 -0.1090 0.6895 0.8830
5.000 0.8411 0.03239 0.02437 -0.1098 0.6878 0.8909
5.250 0.8421 0.03354 0.02562 -0.1065 0.6760 0.9018
5.500 0.8761 0.03283 0.02501 -0.1070 0.6738 0.9121
6.000 0.9137 0.03293 0.02536 -0.1046 0.6594 0.9590
6.500 0.9667 0.03299 0.02561 -0.1052 0.6448 1.0000
6.750 0.9813 0.03388 0.02662 -0.1043 0.6328 1.0000
7.000 1.0216 0.03286 0.02570 -0.1057 0.6295 1.0000
7.500 1.0525 0.03422 0.02727 -0.1037 0.6041 1.0000
7.750 1.0722 0.03455 0.02774 -0.1030 0.5919 1.0000
8.000 1.0951 0.03462 0.02792 -0.1025 0.5798 1.0000
8.250 1.1188 0.03459 0.02801 -0.1020 0.5663 1.0000
8.500 1.1429 0.03453 0.02805 -0.1015 0.5507 1.0000
8.750 1.1701 0.03417 0.02781 -0.1011 0.5331 1.0000
9.000 1.2052 0.03314 0.02680 -0.1012 0.5123 1.0000
9.250 1.2337 0.03271 0.02635 -0.1008 0.4840 1.0000
9.500 1.2590 0.03258 0.02612 -0.1001 0.4495 1.0000
9.750 1.2760 0.03312 0.02653 -0.0986 0.4107 1.0000
10.000 1.2838 0.03439 0.02756 -0.0965 0.3681 1.0000
10.250 1.2848 0.03622 0.02912 -0.0939 0.3234 1.0000
10.500 1.2836 0.03836 0.03100 -0.0914 0.2806 1.0000
10.750 1.2822 0.04065 0.03304 -0.0891 0.2412 1.0000
11.000 1.2808 0.04307 0.03523 -0.0871 0.2026 1.0000
11.250 1.2812 0.04547 0.03742 -0.0853 0.1678 1.0000
11.500 1.2815 0.04798 0.03971 -0.0838 0.1337 1.0000
11.750 1.2833 0.05044 0.04203 -0.0824 0.1054 1.0000
12.000 1.2857 0.05292 0.04439 -0.0812 0.0805 1.0000
12.250 1.2863 0.05566 0.04699 -0.0799 0.0571 1.0000
12.500 1.2870 0.05849 0.04975 -0.0788 0.0419 1.0000
12.750 1.2876 0.06141 0.05267 -0.0777 0.0336 1.0000
13.000 1.2887 0.06435 0.05569 -0.0768 0.0291 1.0000
13.250 1.2887 0.06750 0.05892 -0.0760 0.0265 1.0000
13.500 1.2901 0.07052 0.06213 -0.0753 0.0246 1.0000
13.750 1.2907 0.07370 0.06546 -0.0749 0.0232 1.0000
14.000 1.2905 0.07705 0.06895 -0.0745 0.0221 1.0000
14.250 1.2883 0.08071 0.07275 -0.0743 0.0213 1.0000
14.500 1.2886 0.08412 0.07631 -0.0742 0.0205 1.0000
14.750 1.2901 0.08743 0.07981 -0.0742 0.0196 1.0000
15.000 1.2914 0.09079 0.08333 -0.0744 0.0187 1.0000
15.250 1.2924 0.09424 0.08692 -0.0747 0.0179 1.0000
15.500 1.2931 0.09777 0.09058 -0.0752 0.0173 1.0000
15.750 1.2934 0.10135 0.09427 -0.0758 0.0168 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA NLF1015 (nlf1015-il)