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NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-015A AIRFOIL (n63015a-il)
Reynolds number: 200,000
Max Cl/Cd: 46.56 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63015a-il-200000-n5.txt
Download as CSV file: xf-n63015a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-015A 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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.9324   0.10856   0.10410  -0.0129   1.0000   0.0196
 -16.500  -0.9626   0.09842   0.09371  -0.0189   1.0000   0.0195
 -16.250  -0.9845   0.09057   0.08563  -0.0233   1.0000   0.0195
 -16.000  -1.0018   0.08401   0.07887  -0.0266   1.0000   0.0195
 -15.750  -1.0157   0.07832   0.07298  -0.0292   1.0000   0.0196
 -15.500  -1.0271   0.07330   0.06778  -0.0313   1.0000   0.0197
 -15.250  -1.0361   0.06885   0.06314  -0.0328   1.0000   0.0198
 -15.000  -1.0431   0.06483   0.05894  -0.0340   1.0000   0.0199
 -14.750  -1.0482   0.06120   0.05513  -0.0347   1.0000   0.0201
 -14.500  -1.0513   0.05789   0.05165  -0.0353   1.0000   0.0203
 -14.250  -1.0526   0.05485   0.04844  -0.0355   1.0000   0.0205
 -14.000  -1.0520   0.05208   0.04550  -0.0356   1.0000   0.0207
 -13.750  -1.0497   0.04953   0.04279  -0.0354   1.0000   0.0210
 -13.500  -1.0458   0.04718   0.04027  -0.0351   1.0000   0.0213
 -13.250  -1.0405   0.04503   0.03795  -0.0348   1.0000   0.0217
 -13.000  -1.0339   0.04304   0.03579  -0.0343   1.0000   0.0220
 -12.750  -1.0265   0.04115   0.03380  -0.0337   1.0000   0.0225
 -12.500  -1.0186   0.03938   0.03200  -0.0331   1.0000   0.0229
 -12.250  -1.0098   0.03774   0.03031  -0.0325   1.0000   0.0233
 -12.000  -1.0004   0.03619   0.02869  -0.0318   1.0000   0.0238
 -11.750  -0.9905   0.03468   0.02710  -0.0310   1.0000   0.0243
 -11.500  -0.9802   0.03324   0.02557  -0.0301   1.0000   0.0249
 -11.250  -0.9696   0.03184   0.02409  -0.0292   1.0000   0.0255
 -11.000  -0.9588   0.03051   0.02267  -0.0282   1.0000   0.0261
 -10.750  -0.9476   0.02927   0.02132  -0.0270   1.0000   0.0268
 -10.500  -0.9382   0.02795   0.01996  -0.0257   1.0000   0.0275
 -10.250  -0.9288   0.02673   0.01870  -0.0243   1.0000   0.0283
 -10.000  -0.9180   0.02568   0.01761  -0.0228   1.0000   0.0293
  -9.750  -0.9069   0.02472   0.01660  -0.0211   1.0000   0.0305
  -9.500  -0.8956   0.02386   0.01567  -0.0193   1.0000   0.0319
  -9.250  -0.8858   0.02302   0.01479  -0.0170   1.0000   0.0335
  -9.000  -0.8760   0.02224   0.01401  -0.0147   1.0000   0.0355
  -8.750  -0.8633   0.02157   0.01329  -0.0127   1.0000   0.0379
  -8.500  -0.8512   0.02089   0.01258  -0.0105   1.0000   0.0406
  -8.250  -0.8400   0.02024   0.01195  -0.0081   1.0000   0.0437
  -8.000  -0.8283   0.01972   0.01139  -0.0056   1.0000   0.0474
  -7.750  -0.8194   0.01916   0.01086  -0.0027   1.0000   0.0520
  -7.500  -0.7885   0.01842   0.01015  -0.0042   0.9913   0.0614
  -7.250  -0.7577   0.01770   0.00948  -0.0058   0.9811   0.0748
  -7.000  -0.7277   0.01699   0.00883  -0.0070   0.9700   0.0927
  -6.750  -0.6987   0.01626   0.00821  -0.0081   0.9583   0.1174
  -6.500  -0.6716   0.01549   0.00760  -0.0088   0.9455   0.1507
  -6.250  -0.6467   0.01471   0.00702  -0.0090   0.9315   0.1941
  -6.000  -0.6242   0.01388   0.00644  -0.0087   0.9174   0.2503
  -5.750  -0.6036   0.01310   0.00596  -0.0079   0.9032   0.3174
  -5.500  -0.5825   0.01251   0.00563  -0.0069   0.8898   0.3823
  -5.250  -0.5593   0.01216   0.00541  -0.0061   0.8776   0.4307
  -5.000  -0.5351   0.01194   0.00524  -0.0054   0.8654   0.4646
  -4.750  -0.5099   0.01180   0.00508  -0.0048   0.8538   0.4888
  -4.500  -0.4843   0.01167   0.00492  -0.0043   0.8434   0.5081
  -4.250  -0.4586   0.01158   0.00479  -0.0038   0.8328   0.5250
  -4.000  -0.4328   0.01150   0.00468  -0.0033   0.8227   0.5421
  -3.750  -0.4070   0.01144   0.00458  -0.0028   0.8136   0.5596
  -3.500  -0.3810   0.01139   0.00451  -0.0023   0.8038   0.5749
  -3.250  -0.3546   0.01136   0.00442  -0.0020   0.7954   0.5881
  -3.000  -0.3280   0.01132   0.00433  -0.0017   0.7861   0.6005
  -2.750  -0.3012   0.01129   0.00426  -0.0014   0.7782   0.6102
  -2.500  -0.2741   0.01124   0.00418  -0.0012   0.7694   0.6191
  -2.250  -0.2469   0.01121   0.00409  -0.0010   0.7618   0.6269
  -2.000  -0.2196   0.01118   0.00401  -0.0009   0.7532   0.6345
  -1.750  -0.1922   0.01115   0.00395  -0.0007   0.7461   0.6417
  -1.500  -0.1648   0.01112   0.00388  -0.0006   0.7376   0.6494
  -1.250  -0.1374   0.01110   0.00383  -0.0005   0.7306   0.6562
  -1.000  -0.1100   0.01109   0.00379  -0.0004   0.7225   0.6642
  -0.750  -0.0825   0.01107   0.00376  -0.0003   0.7153   0.6707
  -0.500  -0.0550   0.01106   0.00374  -0.0002   0.7076   0.6785
  -0.250  -0.0275   0.01105   0.00373  -0.0001   0.7002   0.6853
   0.000   0.0000   0.01105   0.00373   0.0000   0.6929   0.6929
   0.250   0.0275   0.01105   0.00373   0.0001   0.6853   0.7002
   0.500   0.0550   0.01106   0.00374   0.0002   0.6785   0.7075
   0.750   0.0825   0.01107   0.00376   0.0003   0.6707   0.7153
   1.000   0.1100   0.01109   0.00379   0.0004   0.6642   0.7225
   1.250   0.1374   0.01110   0.00384   0.0005   0.6562   0.7307
   1.500   0.1648   0.01112   0.00388   0.0006   0.6494   0.7376
   1.750   0.1922   0.01115   0.00395   0.0007   0.6417   0.7462
   2.000   0.2196   0.01118   0.00401   0.0009   0.6345   0.7532
   2.250   0.2469   0.01121   0.00409   0.0010   0.6269   0.7618
   2.500   0.2741   0.01124   0.00418   0.0012   0.6191   0.7694
   2.750   0.3012   0.01129   0.00426   0.0014   0.6102   0.7782
   3.000   0.3280   0.01132   0.00433   0.0017   0.6004   0.7861
   3.250   0.3546   0.01136   0.00442   0.0020   0.5881   0.7954
   3.500   0.3810   0.01139   0.00451   0.0023   0.5750   0.8038
   3.750   0.4070   0.01144   0.00458   0.0028   0.5596   0.8136
   4.000   0.4328   0.01150   0.00468   0.0033   0.5421   0.8228
   4.250   0.4586   0.01158   0.00479   0.0038   0.5250   0.8328
   4.500   0.4843   0.01167   0.00492   0.0043   0.5081   0.8434
   4.750   0.5099   0.01180   0.00508   0.0048   0.4889   0.8539
   5.000   0.5351   0.01194   0.00524   0.0054   0.4646   0.8654
   5.250   0.5593   0.01216   0.00541   0.0061   0.4306   0.8776
   5.500   0.5825   0.01251   0.00563   0.0069   0.3822   0.8898
   5.750   0.6036   0.01310   0.00596   0.0079   0.3174   0.9032
   6.000   0.6242   0.01388   0.00644   0.0087   0.2503   0.9174
   6.250   0.6467   0.01471   0.00702   0.0090   0.1940   0.9316
   6.500   0.6716   0.01549   0.00760   0.0088   0.1506   0.9455
   6.750   0.6987   0.01626   0.00821   0.0081   0.1174   0.9583
   7.000   0.7277   0.01699   0.00883   0.0070   0.0927   0.9700
   7.250   0.7578   0.01770   0.00948   0.0057   0.0748   0.9811
   7.500   0.7886   0.01842   0.01015   0.0042   0.0614   0.9914
   7.750   0.8194   0.01915   0.01086   0.0027   0.0520   1.0000
   8.000   0.8284   0.01972   0.01138   0.0056   0.0474   1.0000
   8.250   0.8400   0.02024   0.01195   0.0080   0.0437   1.0000
   8.500   0.8513   0.02089   0.01258   0.0104   0.0406   1.0000
   8.750   0.8634   0.02156   0.01329   0.0127   0.0379   1.0000
   9.000   0.8761   0.02224   0.01400   0.0147   0.0355   1.0000
   9.250   0.8860   0.02302   0.01479   0.0170   0.0335   1.0000
   9.500   0.8958   0.02386   0.01567   0.0192   0.0319   1.0000
   9.750   0.9072   0.02472   0.01660   0.0211   0.0305   1.0000
  10.000   0.9184   0.02568   0.01761   0.0227   0.0293   1.0000
  10.250   0.9292   0.02673   0.01870   0.0242   0.0283   1.0000
  10.500   0.9387   0.02794   0.01995   0.0256   0.0275   1.0000
  10.750   0.9481   0.02926   0.02132   0.0270   0.0268   1.0000
  11.000   0.9594   0.03051   0.02266   0.0281   0.0261   1.0000
  11.250   0.9703   0.03184   0.02408   0.0291   0.0255   1.0000
  11.500   0.9809   0.03323   0.02556   0.0300   0.0249   1.0000
  11.750   0.9912   0.03467   0.02709   0.0309   0.0243   1.0000
  12.000   1.0012   0.03617   0.02867   0.0317   0.0238   1.0000
  12.250   1.0107   0.03773   0.03029   0.0324   0.0233   1.0000
  12.500   1.0195   0.03937   0.03198   0.0330   0.0229   1.0000
  12.750   1.0274   0.04113   0.03378   0.0336   0.0224   1.0000
  13.000   1.0349   0.04303   0.03577   0.0342   0.0220   1.0000
  13.250   1.0416   0.04501   0.03793   0.0346   0.0216   1.0000
  13.500   1.0469   0.04717   0.04025   0.0350   0.0213   1.0000
  13.750   1.0508   0.04951   0.04277   0.0353   0.0210   1.0000
  14.000   1.0532   0.05206   0.04548   0.0354   0.0207   1.0000
  14.250   1.0539   0.05483   0.04842   0.0354   0.0205   1.0000
  14.500   1.0527   0.05787   0.05163   0.0351   0.0203   1.0000
  14.750   1.0496   0.06118   0.05512   0.0346   0.0201   1.0000
  15.000   1.0445   0.06481   0.05892   0.0338   0.0199   1.0000
  15.250   1.0376   0.06883   0.06312   0.0326   0.0198   1.0000
  15.500   1.0286   0.07328   0.06775   0.0310   0.0197   1.0000
  15.750   1.0173   0.07829   0.07296   0.0290   0.0196   1.0000
  16.000   1.0034   0.08400   0.07886   0.0263   0.0195   1.0000
  16.250   0.9862   0.09056   0.08563   0.0230   0.0195   1.0000
  16.500   0.9642   0.09844   0.09373   0.0186   0.0195   1.0000
  16.750   0.9338   0.10864   0.10419   0.0126   0.0196   1.0000
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