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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
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