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NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-015A AIRFOIL (n63015a-il)
Reynolds number: 500,000
Max Cl/Cd: 66.32 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63015a-il-500000.txt
Download as CSV file: xf-n63015a-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -0.9395   0.12838   0.12551  -0.0006   1.0000   0.0181
 -17.750  -0.9735   0.11666   0.11362  -0.0076   1.0000   0.0180
 -17.500  -1.0019   0.10682   0.10360  -0.0134   1.0000   0.0179
 -17.250  -1.0264   0.09821   0.09480  -0.0184   1.0000   0.0179
 -17.000  -1.0482   0.09055   0.08696  -0.0227   1.0000   0.0179
 -16.750  -1.0675   0.08377   0.07999  -0.0262   1.0000   0.0179
 -16.500  -1.0844   0.07771   0.07375  -0.0291   1.0000   0.0179
 -16.250  -1.0990   0.07233   0.06818  -0.0315   1.0000   0.0179
 -16.000  -1.1118   0.06754   0.06320  -0.0334   1.0000   0.0180
 -15.750  -1.1228   0.06323   0.05871  -0.0348   1.0000   0.0180
 -15.500  -1.1322   0.05937   0.05468  -0.0358   1.0000   0.0181
 -15.250  -1.1424   0.05517   0.05028  -0.0360   1.0000   0.0182
 -15.000  -1.1466   0.05172   0.04667  -0.0357   1.0000   0.0184
 -14.750  -1.1464   0.04888   0.04372  -0.0354   1.0000   0.0185
 -14.500  -1.1435   0.04644   0.04118  -0.0350   1.0000   0.0187
 -14.250  -1.1392   0.04424   0.03889  -0.0347   1.0000   0.0189
 -14.000  -1.1339   0.04219   0.03676  -0.0342   1.0000   0.0191
 -13.750  -1.1275   0.04027   0.03475  -0.0338   1.0000   0.0193
 -13.500  -1.1203   0.03846   0.03285  -0.0332   1.0000   0.0196
 -13.250  -1.1122   0.03673   0.03104  -0.0326   1.0000   0.0199
 -13.000  -1.1032   0.03511   0.02932  -0.0319   1.0000   0.0201
 -12.750  -1.0933   0.03359   0.02771  -0.0311   1.0000   0.0205
 -12.500  -1.0827   0.03213   0.02616  -0.0302   1.0000   0.0208
 -12.250  -1.0714   0.03079   0.02472  -0.0294   1.0000   0.0212
 -12.000  -1.0592   0.02956   0.02340  -0.0286   1.0000   0.0216
 -11.750  -1.0462   0.02847   0.02220  -0.0277   1.0000   0.0219
 -11.500  -1.0366   0.02686   0.02053  -0.0263   1.0000   0.0224
 -11.250  -1.0269   0.02545   0.01910  -0.0250   1.0000   0.0229
 -11.000  -1.0153   0.02432   0.01793  -0.0237   1.0000   0.0233
 -10.750  -1.0029   0.02331   0.01689  -0.0224   1.0000   0.0239
 -10.500  -0.9901   0.02238   0.01592  -0.0210   1.0000   0.0244
 -10.250  -0.9772   0.02151   0.01500  -0.0195   1.0000   0.0251
 -10.000  -0.9641   0.02072   0.01415  -0.0178   1.0000   0.0258
  -9.750  -0.9502   0.02006   0.01341  -0.0160   1.0000   0.0264
  -9.500  -0.9445   0.01905   0.01238  -0.0129   1.0000   0.0272
  -9.250  -0.9336   0.01829   0.01162  -0.0105   1.0000   0.0283
  -9.000  -0.9195   0.01774   0.01105  -0.0085   1.0000   0.0296
  -8.750  -0.9057   0.01726   0.01054  -0.0063   1.0000   0.0310
  -8.500  -0.8965   0.01667   0.00992  -0.0032   1.0000   0.0326
  -8.250  -0.8896   0.01614   0.00940   0.0003   1.0000   0.0345
  -8.000  -0.8665   0.01566   0.00889   0.0006   0.9977   0.0374
  -7.750  -0.8318   0.01487   0.00813  -0.0017   0.9930   0.0430
  -7.500  -0.7975   0.01419   0.00748  -0.0037   0.9869   0.0511
  -7.250  -0.7622   0.01355   0.00691  -0.0059   0.9814   0.0638
  -7.000  -0.7305   0.01288   0.00635  -0.0074   0.9721   0.0835
  -6.750  -0.7008   0.01225   0.00585  -0.0083   0.9606   0.1086
  -6.500  -0.6736   0.01164   0.00539  -0.0087   0.9473   0.1412
  -6.250  -0.6507   0.01098   0.00492  -0.0082   0.9316   0.1856
  -6.000  -0.6309   0.01026   0.00445  -0.0070   0.9150   0.2434
  -5.750  -0.6128   0.00950   0.00401  -0.0055   0.8990   0.3175
  -5.500  -0.5929   0.00894   0.00370  -0.0043   0.8846   0.3864
  -5.250  -0.5701   0.00863   0.00349  -0.0034   0.8717   0.4323
  -5.000  -0.5456   0.00845   0.00334  -0.0027   0.8593   0.4617
  -4.750  -0.5200   0.00832   0.00322  -0.0023   0.8476   0.4840
  -4.500  -0.4942   0.00822   0.00310  -0.0018   0.8372   0.5040
  -4.250  -0.4681   0.00815   0.00301  -0.0015   0.8268   0.5229
  -4.000  -0.4415   0.00809   0.00293  -0.0012   0.8170   0.5382
  -3.750  -0.4147   0.00805   0.00283  -0.0010   0.8079   0.5505
  -3.500  -0.3873   0.00802   0.00276  -0.0008   0.7986   0.5621
  -3.250  -0.3604   0.00799   0.00269  -0.0006   0.7903   0.5735
  -3.000  -0.3333   0.00794   0.00265  -0.0004   0.7813   0.5863
  -2.750  -0.3061   0.00794   0.00260  -0.0003   0.7736   0.5983
  -2.500  -0.2785   0.00793   0.00256  -0.0002   0.7649   0.6094
  -2.000  -0.2235   0.00788   0.00250   0.0000   0.7491   0.6286
  -1.750  -0.1959   0.00788   0.00246   0.0001   0.7417   0.6374
  -1.500  -0.1679   0.00785   0.00243   0.0001   0.7337   0.6450
  -1.250  -0.1400   0.00784   0.00240   0.0001   0.7263   0.6524
  -1.000  -0.1120   0.00783   0.00236   0.0001   0.7187   0.6599
  -0.750  -0.0841   0.00781   0.00235   0.0001   0.7111   0.6670
  -0.250  -0.0280   0.00779   0.00233   0.0000   0.6962   0.6815
   0.000   0.0000   0.00783   0.00231   0.0000   0.6893   0.6893
   0.250   0.0280   0.00779   0.00233   0.0000   0.6815   0.6962
   0.750   0.0841   0.00781   0.00235  -0.0001   0.6670   0.7111
   1.000   0.1120   0.00783   0.00236  -0.0001   0.6599   0.7188
   1.250   0.1400   0.00784   0.00240  -0.0001   0.6524   0.7263
   1.500   0.1679   0.00785   0.00243  -0.0001   0.6450   0.7337
   1.750   0.1959   0.00788   0.00246  -0.0001   0.6373   0.7417
   2.000   0.2235   0.00788   0.00250   0.0000   0.6286   0.7491
   2.500   0.2785   0.00793   0.00256   0.0002   0.6094   0.7649
   2.750   0.3061   0.00794   0.00260   0.0003   0.5984   0.7736
   3.000   0.3333   0.00794   0.00265   0.0004   0.5863   0.7813
   3.250   0.3604   0.00799   0.00269   0.0006   0.5735   0.7903
   3.500   0.3873   0.00802   0.00276   0.0008   0.5622   0.7986
   3.750   0.4147   0.00805   0.00283   0.0010   0.5505   0.8079
   4.000   0.4416   0.00809   0.00293   0.0012   0.5382   0.8170
   4.250   0.4682   0.00815   0.00301   0.0015   0.5229   0.8268
   4.500   0.4942   0.00822   0.00310   0.0018   0.5039   0.8372
   4.750   0.5200   0.00832   0.00322   0.0023   0.4841   0.8476
   5.000   0.5456   0.00845   0.00334   0.0027   0.4617   0.8592
   5.250   0.5701   0.00863   0.00349   0.0033   0.4323   0.8716
   5.500   0.5929   0.00894   0.00370   0.0043   0.3863   0.8846
   5.750   0.6128   0.00950   0.00401   0.0055   0.3173   0.8991
   6.000   0.6309   0.01026   0.00446   0.0070   0.2432   0.9151
   6.250   0.6507   0.01098   0.00492   0.0082   0.1853   0.9316
   6.500   0.6736   0.01164   0.00539   0.0087   0.1411   0.9473
   6.750   0.7009   0.01225   0.00585   0.0083   0.1085   0.9606
   7.000   0.7306   0.01288   0.00635   0.0073   0.0835   0.9721
   7.250   0.7623   0.01355   0.00691   0.0059   0.0638   0.9815
   7.500   0.7976   0.01418   0.00748   0.0037   0.0511   0.9870
   7.750   0.8319   0.01487   0.00813   0.0017   0.0430   0.9931
   8.000   0.8667   0.01566   0.00889  -0.0006   0.0374   0.9977
   8.250   0.8895   0.01614   0.00940  -0.0002   0.0345   1.0000
   8.500   0.8965   0.01667   0.00992   0.0032   0.0326   1.0000
   8.750   0.9057   0.01726   0.01054   0.0063   0.0310   1.0000
   9.000   0.9196   0.01774   0.01105   0.0085   0.0296   1.0000
   9.250   0.9338   0.01829   0.01162   0.0105   0.0283   1.0000
   9.500   0.9449   0.01906   0.01238   0.0128   0.0272   1.0000
   9.750   0.9507   0.02006   0.01342   0.0159   0.0264   1.0000
  10.000   0.9646   0.02073   0.01415   0.0177   0.0258   1.0000
  10.250   0.9778   0.02151   0.01500   0.0193   0.0251   1.0000
  10.500   0.9908   0.02238   0.01592   0.0209   0.0244   1.0000
  10.750   1.0037   0.02332   0.01690   0.0223   0.0239   1.0000
  11.000   1.0162   0.02432   0.01793   0.0235   0.0233   1.0000
  11.250   1.0278   0.02546   0.01910   0.0248   0.0228   1.0000
  11.500   1.0376   0.02686   0.02054   0.0261   0.0224   1.0000
  11.750   1.0473   0.02846   0.02219   0.0275   0.0219   1.0000
  12.000   1.0604   0.02956   0.02340   0.0284   0.0216   1.0000
  12.250   1.0726   0.03078   0.02471   0.0292   0.0212   1.0000
  12.500   1.0839   0.03213   0.02615   0.0301   0.0208   1.0000
  12.750   1.0946   0.03358   0.02770   0.0309   0.0205   1.0000
  13.000   1.1046   0.03510   0.02931   0.0317   0.0201   1.0000
  13.250   1.1136   0.03673   0.03103   0.0324   0.0199   1.0000
  13.500   1.1217   0.03844   0.03284   0.0330   0.0196   1.0000
  13.750   1.1290   0.04026   0.03474   0.0335   0.0193   1.0000
  14.000   1.1354   0.04218   0.03674   0.0340   0.0191   1.0000
  14.250   1.1408   0.04422   0.03887   0.0344   0.0189   1.0000
  14.500   1.1452   0.04642   0.04116   0.0348   0.0187   1.0000
  14.750   1.1481   0.04887   0.04371   0.0352   0.0185   1.0000
  15.000   1.1483   0.05171   0.04666   0.0355   0.0184   1.0000
  15.250   1.1440   0.05517   0.05028   0.0357   0.0182   1.0000
  15.500   1.1338   0.05939   0.05469   0.0355   0.0181   1.0000
  15.750   1.1244   0.06324   0.05873   0.0345   0.0180   1.0000
  16.000   1.1134   0.06755   0.06322   0.0331   0.0180   1.0000
  16.250   1.1006   0.07237   0.06822   0.0312   0.0179   1.0000
  16.500   1.0859   0.07776   0.07380   0.0288   0.0179   1.0000
  16.750   1.0690   0.08386   0.08008   0.0258   0.0178   1.0000
  17.000   1.0496   0.09067   0.08709   0.0222   0.0178   1.0000
  17.250   1.0280   0.09831   0.09491   0.0180   0.0179   1.0000
  17.500   1.0031   0.10703   0.10381   0.0129   0.0179   1.0000
  17.750   0.9743   0.11699   0.11395   0.0070   0.0180   1.0000
  18.000   0.9401   0.12880   0.12594   0.0000   0.0181   1.0000
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