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NACA 1-H-15 AIRFOIL (n1h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 1-H-15 AIRFOIL (n1h15-il)
Reynolds number: 1,000,000
Max Cl/Cd: 133.15 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n1h15-il-1000000-n5.txt
Download as CSV file: xf-n1h15-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1-H-15 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2829   0.08806   0.08525  -0.0506   0.6821   0.0146
 -10.000  -0.3158   0.07870   0.07592  -0.0551   0.6812   0.0158
  -9.750  -0.3221   0.07474   0.07198  -0.0573   0.6802   0.0159
  -9.500  -0.3225   0.07199   0.06924  -0.0591   0.6791   0.0161
  -9.250  -0.3456   0.06720   0.06447  -0.0618   0.6779   0.0161
  -8.750  -0.5391   0.02635   0.02208  -0.0566   0.6753   0.0191
  -8.500  -0.5251   0.02441   0.01992  -0.0552   0.6745   0.0193
  -8.250  -0.5043   0.02348   0.01889  -0.0545   0.6736   0.0194
  -8.000  -0.4831   0.02254   0.01783  -0.0538   0.6726   0.0195
  -7.750  -0.4607   0.02175   0.01693  -0.0533   0.6715   0.0197
  -7.500  -0.4377   0.02102   0.01611  -0.0528   0.6705   0.0198
  -7.250  -0.4141   0.02037   0.01536  -0.0523   0.6695   0.0200
  -7.000  -0.3901   0.01975   0.01465  -0.0519   0.6685   0.0202
  -6.750  -0.3662   0.01904   0.01383  -0.0515   0.6675   0.0204
  -6.500  -0.3429   0.01812   0.01275  -0.0510   0.6665   0.0207
  -6.250  -0.3189   0.01725   0.01174  -0.0505   0.6655   0.0209
  -6.000  -0.2944   0.01641   0.01075  -0.0501   0.6645   0.0211
  -5.750  -0.2692   0.01568   0.00989  -0.0498   0.6634   0.0213
  -5.500  -0.2437   0.01499   0.00906  -0.0495   0.6622   0.0216
  -5.250  -0.2176   0.01441   0.00836  -0.0493   0.6610   0.0218
  -5.000  -0.1910   0.01387   0.00774  -0.0492   0.6602   0.0220
  -4.750  -0.1641   0.01338   0.00718  -0.0492   0.6594   0.0222
  -4.500  -0.1369   0.01296   0.00671  -0.0492   0.6586   0.0224
  -4.250  -0.1094   0.01266   0.00636  -0.0493   0.6576   0.0226
  -4.000  -0.0817   0.01240   0.00606  -0.0494   0.6567   0.0227
  -3.750  -0.0541   0.01210   0.00573  -0.0495   0.6556   0.0229
  -3.500  -0.0278   0.01146   0.00505  -0.0493   0.6545   0.0232
  -3.250  -0.0007   0.01110   0.00467  -0.0494   0.6533   0.0235
  -3.000   0.0266   0.01084   0.00440  -0.0494   0.6522   0.0238
  -2.750   0.0541   0.01061   0.00416  -0.0495   0.6511   0.0240
  -2.500   0.0816   0.01039   0.00393  -0.0495   0.6501   0.0242
  -2.250   0.1091   0.01021   0.00373  -0.0496   0.6491   0.0246
  -2.000   0.1365   0.01002   0.00354  -0.0497   0.6481   0.0248
  -1.750   0.1640   0.00986   0.00336  -0.0497   0.6470   0.0251
  -1.500   0.1916   0.00971   0.00320  -0.0499   0.6460   0.0254
  -1.250   0.2194   0.00956   0.00307  -0.0500   0.6451   0.0257
  -1.000   0.2474   0.00943   0.00295  -0.0502   0.6440   0.0261
  -0.750   0.2754   0.00931   0.00284  -0.0504   0.6428   0.0265
  -0.500   0.3034   0.00921   0.00275  -0.0506   0.6417   0.0269
  -0.250   0.3316   0.00914   0.00269  -0.0509   0.6406   0.0273
   0.000   0.3594   0.00903   0.00259  -0.0511   0.6395   0.0278
   0.250   0.3872   0.00892   0.00249  -0.0513   0.6384   0.0285
   0.500   0.4152   0.00885   0.00243  -0.0515   0.6372   0.0292
   0.750   0.4434   0.00879   0.00238  -0.0518   0.6360   0.0300
   1.000   0.4714   0.00874   0.00234  -0.0520   0.6348   0.0308
   1.250   0.4995   0.00871   0.00231  -0.0523   0.6335   0.0318
   1.500   0.5275   0.00869   0.00229  -0.0525   0.6323   0.0328
   1.750   0.5558   0.00867   0.00231  -0.0529   0.6314   0.0352
   2.000   0.5839   0.00863   0.00235  -0.0532   0.6303   0.0457
   2.250   0.6087   0.00831   0.00243  -0.0530   0.6291   0.2010
   2.750   0.7147   0.00682   0.00307  -0.0649   0.6269   0.9725
   3.000   0.7633   0.00696   0.00321  -0.0696   0.6246   0.9759
   3.250   0.8049   0.00710   0.00333  -0.0729   0.6212   0.9808
   3.500   0.8444   0.00723   0.00343  -0.0756   0.6184   0.9847
   3.750   0.8803   0.00729   0.00351  -0.0778   0.6164   0.9857
   4.000   0.9128   0.00736   0.00361  -0.0792   0.6127   0.9863
   4.250   0.9445   0.00743   0.00370  -0.0805   0.6095   0.9870
   4.500   0.9757   0.00750   0.00378  -0.0816   0.6064   0.9877
   4.750   1.0066   0.00761   0.00388  -0.0828   0.6019   0.9884
   5.000   1.0386   0.00780   0.00409  -0.0843   0.5927   0.9891
   5.250   1.0712   0.00811   0.00438  -0.0862   0.5787   0.9898
   5.500   1.1045   0.00886   0.00503  -0.0890   0.5500   0.9905
   5.750   1.1272   0.01152   0.00734  -0.0927   0.4783   0.9931
   6.000   1.0993   0.01603   0.01135  -0.0898   0.3819   1.0000
   6.250   1.0644   0.01788   0.01304  -0.0805   0.3485   1.0000
   6.500   1.0283   0.02039   0.01525  -0.0720   0.2937   1.0000
   6.750   0.9959   0.02313   0.01762  -0.0646   0.2219   1.0000
   7.000   0.9800   0.02530   0.01950  -0.0596   0.1647   1.0000
   7.250   0.9788   0.02678   0.02080  -0.0565   0.1297   1.0000
   7.500   0.9818   0.02808   0.02197  -0.0539   0.1029   1.0000
   7.750   0.9873   0.02926   0.02304  -0.0516   0.0794   1.0000
   8.000   0.9929   0.03050   0.02416  -0.0495   0.0582   1.0000
   8.250   1.0025   0.03152   0.02512  -0.0478   0.0477   1.0000
   8.500   1.0143   0.03242   0.02599  -0.0464   0.0421   1.0000
   8.750   1.0278   0.03321   0.02678  -0.0451   0.0392   1.0000
   9.000   1.0409   0.03405   0.02762  -0.0439   0.0375   1.0000
   9.250   1.0530   0.03499   0.02855  -0.0426   0.0354   1.0000
   9.500   1.0660   0.03586   0.02944  -0.0414   0.0341   1.0000
   9.750   1.0800   0.03667   0.03027  -0.0404   0.0334   1.0000
  10.000   1.0938   0.03751   0.03112  -0.0393   0.0328   1.0000
  10.250   1.1070   0.03840   0.03202  -0.0382   0.0319   1.0000
  10.500   1.1193   0.03939   0.03302  -0.0371   0.0311   1.0000
  10.750   1.1318   0.04036   0.03400  -0.0360   0.0303   1.0000
  11.000   1.1442   0.04135   0.03501  -0.0350   0.0293   1.0000
  11.250   1.1557   0.04241   0.03608  -0.0339   0.0283   1.0000
  11.500   1.1683   0.04341   0.03710  -0.0329   0.0279   1.0000
  11.750   1.1809   0.04443   0.03815  -0.0320   0.0275   1.0000
  12.000   1.1938   0.04543   0.03918  -0.0311   0.0270   1.0000
  12.250   1.2066   0.04644   0.04022  -0.0302   0.0264   1.0000
  12.500   1.2193   0.04747   0.04128  -0.0293   0.0259   1.0000
  12.750   1.2308   0.04862   0.04246  -0.0285   0.0255   1.0000
  13.000   1.2422   0.04977   0.04363  -0.0276   0.0247   1.0000
  13.250   1.2529   0.05100   0.04485  -0.0267   0.0236   1.0000
  13.500   1.2634   0.05225   0.04613  -0.0258   0.0230   1.0000
  13.750   1.2750   0.05343   0.04735  -0.0250   0.0229   1.0000
  14.000   1.2869   0.05461   0.04858  -0.0243   0.0224   1.0000
  14.250   1.2980   0.05585   0.04986  -0.0236   0.0218   1.0000
  14.500   1.3094   0.05706   0.05111  -0.0229   0.0213   1.0000
  14.750   1.3208   0.05828   0.05236  -0.0223   0.0207   1.0000
  15.000   1.3311   0.05962   0.05371  -0.0216   0.0200   1.0000
  15.250   1.3407   0.06104   0.05516  -0.0209   0.0194   1.0000
  15.500   1.3498   0.06251   0.05665  -0.0202   0.0188   1.0000
  15.750   1.3610   0.06379   0.05798  -0.0197   0.0183   1.0000
  16.000   1.3707   0.06523   0.05947  -0.0191   0.0176   1.0000
  16.250   1.3796   0.06677   0.06104  -0.0185   0.0170   1.0000
  16.500   1.3889   0.06824   0.06254  -0.0180   0.0163   1.0000
  16.750   1.3979   0.06975   0.06407  -0.0175   0.0156   1.0000
  17.000   1.4052   0.07148   0.06583  -0.0169   0.0151   1.0000
  17.250   1.4128   0.07318   0.06760  -0.0164   0.0147   1.0000
  17.500   1.4210   0.07483   0.06929  -0.0160   0.0141   1.0000
  17.750   1.4286   0.07655   0.07105  -0.0156   0.0134   1.0000
  18.000   1.4346   0.07848   0.07302  -0.0152   0.0129   1.0000
  18.250   1.4405   0.08039   0.07496  -0.0148   0.0124   1.0000
  18.500   1.4465   0.08232   0.07694  -0.0145   0.0119   1.0000
  18.750   1.4516   0.08439   0.07908  -0.0142   0.0116   1.0000
  19.000   1.4566   0.08648   0.08123  -0.0139   0.0113   1.0000
  19.250   1.4613   0.08861   0.08342  -0.0138   0.0109   1.0000
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