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NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il)
Reynolds number: 200,000
Max Cl/Cd: 76.86 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf0215f-il-200000-n5.txt
Download as CSV file: xf-nlf0215f-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY NLF(1)-0215F AIRFOIL               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2498   0.08820   0.08461  -0.0773   0.9582   0.0214
  -9.500  -0.2474   0.08329   0.07972  -0.0806   0.9439   0.0210
  -9.000  -0.2876   0.05605   0.05216  -0.1059   0.9118   0.0177
  -8.750  -0.2904   0.04962   0.04543  -0.1131   0.8946   0.0176
  -8.500  -0.2779   0.04374   0.03915  -0.1205   0.8790   0.0175
  -8.250  -0.2660   0.03812   0.03290  -0.1252   0.8627   0.0177
  -8.000  -0.2474   0.03427   0.02855  -0.1281   0.8474   0.0181
  -7.750  -0.2213   0.03258   0.02672  -0.1303   0.8333   0.0186
  -7.500  -0.2005   0.03010   0.02384  -0.1312   0.8197   0.0188
  -7.250  -0.1804   0.02742   0.02064  -0.1315   0.8074   0.0187
  -7.000  -0.1578   0.02546   0.01828  -0.1316   0.7963   0.0187
  -6.750  -0.1349   0.02394   0.01648  -0.1314   0.7861   0.0189
  -6.500  -0.1101   0.02262   0.01488  -0.1314   0.7775   0.0190
  -6.250  -0.0862   0.02150   0.01355  -0.1310   0.7687   0.0193
  -6.000  -0.0609   0.02052   0.01237  -0.1308   0.7612   0.0197
  -5.750  -0.0368   0.01965   0.01135  -0.1303   0.7532   0.0200
  -5.250   0.0124   0.01820   0.00965  -0.1293   0.7395   0.0211
  -5.000   0.0376   0.01769   0.00900  -0.1290   0.7334   0.0221
  -4.750   0.0621   0.01708   0.00839  -0.1288   0.7282   0.0233
  -4.500   0.0867   0.01661   0.00789  -0.1285   0.7225   0.0245
  -4.250   0.1123   0.01614   0.00736  -0.1284   0.7174   0.0255
  -4.000   0.1388   0.01572   0.00684  -0.1285   0.7129   0.0266
  -3.750   0.1648   0.01530   0.00638  -0.1286   0.7076   0.0281
  -3.500   0.1919   0.01497   0.00600  -0.1289   0.7028   0.0303
  -3.250   0.2200   0.01469   0.00565  -0.1292   0.6989   0.0347
  -2.750   0.2763   0.01378   0.00504  -0.1306   0.6908   0.1101
  -2.500   0.3069   0.01281   0.00476  -0.1327   0.6868   0.2964
  -2.250   0.3266   0.01275   0.00604  -0.1305   0.6833   0.6469
  -2.000   0.3539   0.01350   0.00667  -0.1297   0.6798   0.6918
  -1.750   0.3757   0.01419   0.00734  -0.1274   0.6760   0.7127
  -1.500   0.3957   0.01478   0.00792  -0.1248   0.6725   0.7282
  -1.250   0.4169   0.01511   0.00820  -0.1226   0.6691   0.7354
  -1.000   0.4480   0.01513   0.00808  -0.1236   0.6661   0.7407
  -0.750   0.4765   0.01513   0.00799  -0.1240   0.6628   0.7432
  -0.500   0.5029   0.01515   0.00798  -0.1238   0.6594   0.7449
  -0.250   0.5301   0.01517   0.00794  -0.1238   0.6561   0.7466
   0.000   0.5583   0.01519   0.00789  -0.1240   0.6530   0.7483
   0.250   0.5877   0.01522   0.00784  -0.1246   0.6502   0.7501
   0.500   0.6168   0.01524   0.00782  -0.1252   0.6474   0.7520
   0.750   0.6456   0.01526   0.00782  -0.1257   0.6439   0.7539
   1.000   0.6755   0.01528   0.00780  -0.1266   0.6406   0.7558
   1.250   0.7063   0.01530   0.00778  -0.1276   0.6376   0.7573
   1.500   0.7350   0.01535   0.00778  -0.1280   0.6349   0.7583
   1.750   0.7633   0.01541   0.00782  -0.1283   0.6322   0.7593
   2.000   0.7898   0.01547   0.00792  -0.1283   0.6287   0.7602
   2.250   0.8173   0.01553   0.00800  -0.1285   0.6253   0.7610
   2.500   0.8453   0.01559   0.00807  -0.1287   0.6220   0.7619
   2.750   0.8739   0.01566   0.00813  -0.1291   0.6190   0.7631
   3.000   0.9027   0.01575   0.00822  -0.1296   0.6160   0.7641
   3.250   0.9289   0.01583   0.00837  -0.1296   0.6116   0.7650
   3.500   0.9563   0.01589   0.00846  -0.1298   0.6072   0.7659
   3.750   0.9848   0.01594   0.00851  -0.1301   0.6029   0.7668
   4.000   1.0117   0.01602   0.00862  -0.1302   0.5978   0.7680
   4.250   1.0375   0.01607   0.00873  -0.1301   0.5914   0.7692
   4.500   1.0659   0.01610   0.00875  -0.1304   0.5858   0.7701
   4.750   1.0909   0.01618   0.00891  -0.1302   0.5791   0.7709
   5.000   1.1171   0.01622   0.00898  -0.1301   0.5723   0.7718
   5.250   1.1429   0.01628   0.00908  -0.1299   0.5649   0.7726
   5.500   1.1669   0.01633   0.00920  -0.1294   0.5568   0.7732
   5.750   1.1906   0.01640   0.00934  -0.1288   0.5489   0.7740
   6.000   1.2136   0.01647   0.00947  -0.1280   0.5400   0.7749
   6.250   1.2356   0.01657   0.00967  -0.1270   0.5300   0.7758
   6.500   1.2575   0.01666   0.00981  -0.1261   0.5192   0.7766
   6.750   1.2784   0.01677   0.00996  -0.1250   0.5065   0.7773
   7.000   1.2979   0.01692   0.01016  -0.1236   0.4910   0.7782
   7.250   1.3158   0.01712   0.01039  -0.1219   0.4718   0.7790
   7.500   1.3307   0.01739   0.01062  -0.1197   0.4485   0.7799
   7.750   1.3409   0.01777   0.01092  -0.1166   0.4220   0.7809
   8.000   1.3474   0.01836   0.01138  -0.1131   0.3917   0.7819
   8.250   1.3512   0.01919   0.01206  -0.1093   0.3593   0.7829
   8.500   1.3533   0.02019   0.01291  -0.1055   0.3283   0.7841
   8.750   1.3554   0.02128   0.01389  -0.1019   0.3007   0.7854
   9.000   1.3567   0.02251   0.01501  -0.0985   0.2755   0.7867
   9.250   1.3592   0.02380   0.01622  -0.0954   0.2523   0.7878
   9.500   1.3604   0.02520   0.01756  -0.0925   0.2322   0.7886
   9.750   1.3628   0.02664   0.01898  -0.0899   0.2138   0.7894
  10.000   1.3655   0.02818   0.02050  -0.0876   0.1968   0.7902
  10.250   1.3685   0.02980   0.02211  -0.0855   0.1814   0.7911
  10.500   1.3718   0.03151   0.02380  -0.0837   0.1675   0.7920
  10.750   1.3752   0.03331   0.02560  -0.0820   0.1547   0.7929
  11.000   1.3785   0.03520   0.02749  -0.0805   0.1434   0.7939
  11.250   1.3840   0.03701   0.02934  -0.0794   0.1326   0.7948
  11.500   1.3893   0.03889   0.03126  -0.0783   0.1237   0.7958
  11.750   1.3929   0.04099   0.03336  -0.0772   0.1154   0.7968
  12.000   1.3996   0.04287   0.03531  -0.0764   0.1076   0.7978
  12.250   1.4037   0.04503   0.03750  -0.0756   0.1010   0.7988
  12.500   1.4098   0.04707   0.03960  -0.0750   0.0943   0.7999
  12.750   1.4136   0.04939   0.04194  -0.0743   0.0889   0.8009
  13.000   1.4203   0.05147   0.04413  -0.0739   0.0836   0.8021
  13.500   1.4291   0.05618   0.04897  -0.0730   0.0748   0.8043
  13.750   1.4341   0.05854   0.05142  -0.0726   0.0706   0.8054
  14.000   1.4361   0.06129   0.05421  -0.0724   0.0670   0.8065
  14.250   1.4416   0.06368   0.05672  -0.0722   0.0638   0.8077
  14.500   1.4464   0.06622   0.05936  -0.0721   0.0605   0.8088
  14.750   1.4485   0.06914   0.06234  -0.0721   0.0573   0.8099
  15.000   1.4518   0.07195   0.06525  -0.0722   0.0543   0.8111
  15.250   1.4567   0.07462   0.06803  -0.0724   0.0510   0.8124
  15.500   1.4583   0.07776   0.07123  -0.0727   0.0480   0.8136
  15.750   1.4600   0.08094   0.07449  -0.0731   0.0454   0.8148
  16.000   1.4642   0.08383   0.07752  -0.0736   0.0427   0.8162
  16.250   1.4656   0.08718   0.08095  -0.0742   0.0404   0.8175
  16.500   1.4637   0.09102   0.08485  -0.0750   0.0385   0.8187
  16.750   1.4666   0.09417   0.08818  -0.0756   0.0366   0.8199
  17.000   1.4679   0.09761   0.09176  -0.0764   0.0347   0.8213
  17.250   1.4669   0.10144   0.09570  -0.0775   0.0330   0.8227
  17.500   1.4634   0.10575   0.10009  -0.0789   0.0315   0.8241
  17.750   1.4640   0.10945   0.10394  -0.0800   0.0299   0.8257
  18.000   1.4634   0.11340   0.10804  -0.0815   0.0283   0.8274
  18.250   1.4608   0.11774   0.11250  -0.0832   0.0269   0.8291
  18.500   1.4559   0.12251   0.11737  -0.0852   0.0258   0.8308
  18.750   1.4527   0.12704   0.12203  -0.0872   0.0247   0.8326
  19.000   1.4501   0.13148   0.12664  -0.0893   0.0234   0.8344
  19.250   1.4461   0.13622   0.13152  -0.0916   0.0223   0.8363
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