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NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il)
Reynolds number: 500,000
Max Cl/Cd: 110.84 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf0215f-il-500000.txt
Download as CSV file: xf-nlf0215f-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1520   0.10511   0.10292  -0.0716   0.9866   0.0220
 -11.250  -0.1418   0.10103   0.09883  -0.0747   0.9853   0.0226
 -11.000  -0.2968   0.10853   0.10627  -0.0597   0.9957   0.0210
 -10.750  -0.2796   0.10530   0.10303  -0.0628   0.9943   0.0213
 -10.500  -0.2629   0.10227   0.10000  -0.0657   0.9920   0.0218
 -10.250  -0.2505   0.09760   0.09533  -0.0702   0.9893   0.0221
 -10.000  -0.1538   0.07113   0.06898  -0.0914   0.9516   0.0256
  -9.750  -0.1448   0.06745   0.06529  -0.0931   0.9402   0.0259
  -9.500  -0.1312   0.06301   0.06083  -0.0970   0.9314   0.0262
  -9.250  -0.1161   0.05739   0.05518  -0.1032   0.9238   0.0268
  -9.000  -0.1147   0.04722   0.04496  -0.1152   0.9165   0.0270
  -8.750  -0.1186   0.03649   0.03401  -0.1304   0.9038   0.0273
  -8.500  -0.1190   0.03065   0.02783  -0.1384   0.8714   0.0277
  -8.250  -0.1299   0.02788   0.02474  -0.1387   0.8393   0.0283
  -8.000  -0.1508   0.02538   0.02157  -0.1365   0.8143   0.0307
  -7.750  -0.1594   0.02041   0.01625  -0.1354   0.7990   0.0313
  -7.500  -0.1435   0.01849   0.01432  -0.1352   0.7871   0.0319
  -7.250  -0.1282   0.01704   0.01275  -0.1347   0.7759   0.0326
  -7.000  -0.1129   0.01560   0.01117  -0.1342   0.7655   0.0338
  -6.750  -0.0939   0.01575   0.01079  -0.1328   0.7554   0.0373
  -6.500  -0.0876   0.02106   0.01504  -0.1385   0.7660   0.0261
  -6.250  -0.0639   0.01921   0.01305  -0.1379   0.7574   0.0235
  -6.000  -0.0399   0.01794   0.01155  -0.1373   0.7492   0.0236
  -5.750  -0.0157   0.01650   0.00988  -0.1366   0.7423   0.0228
  -5.500   0.0086   0.01540   0.00861  -0.1358   0.7353   0.0223
  -5.250   0.0335   0.01468   0.00777  -0.1353   0.7293   0.0225
  -5.000   0.0583   0.01406   0.00711  -0.1348   0.7233   0.0227
  -4.750   0.0834   0.01355   0.00655  -0.1344   0.7173   0.0234
  -4.500   0.1096   0.01313   0.00603  -0.1343   0.7121   0.0241
  -4.250   0.1358   0.01271   0.00559  -0.1343   0.7072   0.0247
  -4.000   0.1628   0.01237   0.00521  -0.1344   0.7024   0.0253
  -3.750   0.1902   0.01184   0.00465  -0.1348   0.6981   0.0272
  -3.500   0.2188   0.01161   0.00438  -0.1353   0.6940   0.0293
  -3.250   0.2472   0.01131   0.00406  -0.1357   0.6898   0.0313
  -3.000   0.2760   0.01103   0.00376  -0.1361   0.6856   0.0363
  -2.750   0.3070   0.01035   0.00341  -0.1376   0.6819   0.1243
  -2.500   0.3463   0.00852   0.00331  -0.1426   0.6785   0.6198
  -2.250   0.3743   0.00883   0.00361  -0.1423   0.6751   0.6677
  -2.000   0.4017   0.00917   0.00392  -0.1419   0.6715   0.6849
  -1.750   0.4273   0.00966   0.00440  -0.1408   0.6680   0.6999
  -1.500   0.4522   0.01020   0.00491  -0.1396   0.6650   0.7130
  -1.250   0.4772   0.01080   0.00548  -0.1383   0.6619   0.7260
  -1.000   0.4958   0.01128   0.00605  -0.1353   0.6589   0.7332
  -0.750   0.5219   0.01155   0.00630  -0.1347   0.6557   0.7426
  -0.500   0.5453   0.01171   0.00647  -0.1333   0.6528   0.7456
  -0.250   0.5726   0.01178   0.00649  -0.1332   0.6499   0.7480
   0.000   0.6023   0.01186   0.00649  -0.1337   0.6470   0.7502
   0.250   0.6320   0.01186   0.00646  -0.1344   0.6443   0.7525
   0.500   0.6627   0.01184   0.00641  -0.1354   0.6414   0.7548
   0.750   0.6941   0.01183   0.00636  -0.1366   0.6384   0.7568
   1.000   0.7219   0.01178   0.00630  -0.1367   0.6355   0.7578
   1.250   0.7504   0.01179   0.00628  -0.1370   0.6329   0.7587
   1.500   0.7798   0.01189   0.00633  -0.1375   0.6299   0.7596
   1.750   0.8068   0.01187   0.00635  -0.1375   0.6272   0.7606
   2.000   0.8347   0.01187   0.00637  -0.1377   0.6240   0.7615
   2.250   0.8631   0.01187   0.00637  -0.1380   0.6205   0.7624
   2.500   0.8917   0.01189   0.00637  -0.1383   0.6170   0.7636
   2.750   0.9212   0.01197   0.00641  -0.1389   0.6131   0.7645
   3.000   0.9481   0.01192   0.00641  -0.1390   0.6086   0.7653
   3.250   0.9759   0.01189   0.00638  -0.1392   0.6037   0.7662
   3.500   1.0047   0.01192   0.00638  -0.1396   0.5992   0.7673
   3.750   1.0326   0.01194   0.00643  -0.1399   0.5947   0.7682
   4.000   1.0596   0.01191   0.00642  -0.1399   0.5893   0.7689
   4.250   1.0874   0.01191   0.00641  -0.1402   0.5840   0.7696
   4.500   1.1151   0.01195   0.00646  -0.1404   0.5789   0.7702
   4.750   1.1418   0.01194   0.00650  -0.1404   0.5732   0.7711
   5.000   1.1691   0.01198   0.00652  -0.1405   0.5674   0.7719
   5.250   1.1949   0.01198   0.00658  -0.1404   0.5612   0.7724
   5.500   1.2201   0.01195   0.00660  -0.1400   0.5542   0.7729
   5.750   1.2454   0.01199   0.00664  -0.1397   0.5474   0.7734
   6.000   1.2696   0.01198   0.00671  -0.1391   0.5386   0.7739
   6.250   1.2939   0.01203   0.00678  -0.1386   0.5301   0.7745
   6.500   1.3171   0.01209   0.00686  -0.1379   0.5196   0.7750
   6.750   1.3398   0.01216   0.00698  -0.1371   0.5070   0.7757
   7.000   1.3611   0.01228   0.00711  -0.1359   0.4919   0.7766
   7.250   1.3798   0.01248   0.00727  -0.1344   0.4722   0.7774
   7.500   1.3966   0.01278   0.00751  -0.1325   0.4459   0.7780
   7.750   1.4071   0.01324   0.00784  -0.1294   0.4142   0.7787
   8.000   1.4130   0.01389   0.00831  -0.1256   0.3781   0.7795
   8.250   1.4188   0.01470   0.00894  -0.1219   0.3410   0.7802
   8.500   1.4238   0.01560   0.00966  -0.1183   0.3067   0.7810
   8.750   1.4291   0.01652   0.01044  -0.1148   0.2763   0.7818
   9.000   1.4345   0.01746   0.01126  -0.1115   0.2496   0.7826
   9.500   1.4455   0.01947   0.01309  -0.1054   0.2051   0.7841
   9.750   1.4509   0.02056   0.01410  -0.1026   0.1862   0.7850
  10.000   1.4557   0.02176   0.01524  -0.0999   0.1692   0.7859
  10.250   1.4606   0.02302   0.01645  -0.0974   0.1543   0.7867
  10.500   1.4659   0.02435   0.01774  -0.0951   0.1412   0.7873
  10.750   1.4717   0.02571   0.01909  -0.0931   0.1299   0.7880
  11.000   1.4766   0.02719   0.02057  -0.0912   0.1196   0.7887
  11.250   1.4800   0.02887   0.02223  -0.0892   0.1099   0.7894
  11.500   1.4869   0.03038   0.02378  -0.0878   0.1016   0.7901
  11.750   1.4916   0.03212   0.02554  -0.0862   0.0944   0.7909
  12.000   1.4966   0.03391   0.02733  -0.0849   0.0875   0.7917
  12.250   1.5020   0.03573   0.02919  -0.0837   0.0813   0.7925
  12.500   1.5065   0.03768   0.03114  -0.0826   0.0752   0.7933
  12.750   1.5121   0.03960   0.03310  -0.0816   0.0701   0.7942
  13.000   1.5176   0.04157   0.03510  -0.0807   0.0654   0.7950
  13.250   1.5203   0.04387   0.03743  -0.0798   0.0611   0.7959
  13.500   1.5282   0.04571   0.03935  -0.0792   0.0578   0.7968
  13.750   1.5324   0.04796   0.04163  -0.0785   0.0545   0.7977
  14.000   1.5341   0.05056   0.04427  -0.0779   0.0515   0.7986
  14.250   1.5422   0.05251   0.04631  -0.0775   0.0491   0.7995
  14.500   1.5470   0.05485   0.04871  -0.0772   0.0466   0.8005
  14.750   1.5480   0.05768   0.05157  -0.0768   0.0440   0.8015
  15.000   1.5529   0.06013   0.05411  -0.0766   0.0420   0.8025
  15.250   1.5593   0.06243   0.05650  -0.0765   0.0398   0.8036
  15.500   1.5626   0.06512   0.05924  -0.0764   0.0377   0.8046
  15.750   1.5602   0.06861   0.06278  -0.0765   0.0356   0.8055
  16.000   1.5678   0.07088   0.06517  -0.0766   0.0339   0.8066
  16.250   1.5718   0.07364   0.06801  -0.0768   0.0320   0.8077
  16.500   1.5714   0.07707   0.07149  -0.0771   0.0302   0.8087
  16.750   1.5722   0.08038   0.07489  -0.0775   0.0285   0.8098
  17.000   1.5756   0.08339   0.07801  -0.0780   0.0266   0.8110
  17.250   1.5744   0.08712   0.08179  -0.0787   0.0249   0.8121
  17.500   1.5715   0.09115   0.08592  -0.0795   0.0232   0.8132
  17.750   1.5727   0.09466   0.08953  -0.0803   0.0216   0.8144
  18.000   1.5685   0.09903   0.09396  -0.0815   0.0202   0.8155
  18.250   1.5619   0.10386   0.09889  -0.0829   0.0189   0.8165
  18.500   1.5607   0.10790   0.10305  -0.0842   0.0177   0.8176
  18.750   1.5566   0.11245   0.10769  -0.0859   0.0167   0.8188
  19.000   1.5473   0.11794   0.11327  -0.0880   0.0159   0.8198
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