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NACA 6-H-15 AIRFOIL (n6h15-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 6-H-15 AIRFOIL (n6h15-il)
Reynolds number: 200,000
Max Cl/Cd: 53.11 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n6h15-il-200000-n5.txt
Download as CSV file: xf-n6h15-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 6-H-15 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3483   0.09255   0.08792  -0.0308   0.6370   0.0193
  -9.750  -0.3528   0.08801   0.08342  -0.0336   0.6351   0.0193
  -9.500  -0.3593   0.08348   0.07892  -0.0369   0.6333   0.0198
  -9.250  -0.3723   0.07849   0.07393  -0.0398   0.6315   0.0198
  -9.000  -0.3901   0.07357   0.06898  -0.0410   0.6299   0.0194
  -8.750  -0.4042   0.06977   0.06512  -0.0402   0.6282   0.0195
  -8.500  -0.4165   0.06656   0.06181  -0.0383   0.6267   0.0200
  -8.250  -0.4260   0.06250   0.05761  -0.0367   0.6254   0.0200
  -8.000  -0.4326   0.05834   0.05325  -0.0346   0.6241   0.0202
  -7.750  -0.4368   0.05393   0.04864  -0.0323   0.6226   0.0204
  -7.500  -0.4395   0.04912   0.04356  -0.0295   0.6208   0.0207
  -7.250  -0.4610   0.03824   0.03175  -0.0227   0.6197   0.0222
  -7.000  -0.4469   0.03658   0.02992  -0.0212   0.6176   0.0229
  -6.750  -0.4265   0.03623   0.02953  -0.0206   0.6155   0.0236
  -6.500  -0.4113   0.03406   0.02707  -0.0188   0.6138   0.0244
  -6.250  -0.3966   0.03102   0.02354  -0.0166   0.6123   0.0255
  -6.000  -0.3786   0.02812   0.01990  -0.0145   0.6108   0.0275
  -5.750  -0.3563   0.02684   0.01845  -0.0138   0.6094   0.0287
  -5.500  -0.3323   0.02593   0.01739  -0.0134   0.6079   0.0298
  -5.250  -0.3065   0.02485   0.01614  -0.0131   0.6056   0.0309
  -5.000  -0.2798   0.02391   0.01497  -0.0130   0.6034   0.0328
  -4.750  -0.2523   0.02308   0.01385  -0.0129   0.6014   0.0343
  -4.500  -0.2224   0.02181   0.01247  -0.0134   0.5996   0.0356
  -4.250  -0.1942   0.02114   0.01175  -0.0137   0.5980   0.0371
  -4.000  -0.1659   0.02058   0.01111  -0.0140   0.5965   0.0389
  -3.750  -0.1366   0.01995   0.01038  -0.0143   0.5952   0.0404
  -3.500  -0.1074   0.01936   0.00968  -0.0146   0.5940   0.0416
  -3.250  -0.0792   0.01896   0.00916  -0.0148   0.5929   0.0430
  -3.000  -0.0511   0.01834   0.00860  -0.0151   0.5911   0.0450
  -2.750  -0.0244   0.01797   0.00826  -0.0151   0.5894   0.0465
  -2.500   0.0016   0.01767   0.00796  -0.0150   0.5877   0.0481
  -2.250   0.0270   0.01742   0.00770  -0.0147   0.5861   0.0499
  -2.000   0.0523   0.01722   0.00747  -0.0144   0.5846   0.0524
  -1.750   0.0768   0.01698   0.00722  -0.0139   0.5831   0.0557
  -1.500   0.1013   0.01678   0.00702  -0.0134   0.5817   0.0600
  -1.250   0.1259   0.01661   0.00683  -0.0129   0.5804   0.0663
  -1.000   0.1497   0.01641   0.00670  -0.0123   0.5793   0.0841
  -0.750   0.1734   0.01623   0.00660  -0.0117   0.5783   0.1210
  -0.500   0.1949   0.01593   0.00652  -0.0107   0.5773   0.1877
  -0.250   0.1817   0.01430   0.00650  -0.0032   0.5758   0.6033
   0.250   0.3139   0.01705   0.00986  -0.0149   0.5723   0.9111
   0.750   0.4349   0.01797   0.01062  -0.0274   0.5685   0.9324
   1.000   0.4776   0.01812   0.01070  -0.0306   0.5671   0.9379
   1.250   0.5044   0.01821   0.01075  -0.0306   0.5658   0.9418
   1.500   0.5247   0.01827   0.01077  -0.0294   0.5646   0.9440
   1.750   0.5451   0.01831   0.01077  -0.0283   0.5636   0.9450
   2.000   0.5694   0.01831   0.01073  -0.0279   0.5627   0.9452
   2.250   0.5932   0.01838   0.01080  -0.0276   0.5613   0.9453
   2.500   0.6164   0.01858   0.01107  -0.0274   0.5591   0.9455
   2.750   0.6396   0.01876   0.01128  -0.0271   0.5571   0.9458
   3.000   0.6630   0.01891   0.01147  -0.0268   0.5554   0.9460
   3.250   0.6864   0.01906   0.01165  -0.0266   0.5539   0.9463
   3.500   0.7097   0.01919   0.01182  -0.0262   0.5526   0.9466
   3.750   0.7344   0.01932   0.01197  -0.0262   0.5513   0.9470
   4.000   0.7600   0.01934   0.01201  -0.0261   0.5499   0.9475
   4.250   0.7858   0.01909   0.01171  -0.0258   0.5478   0.9478
   4.500   0.8079   0.01919   0.01188  -0.0252   0.5443   0.9482
   4.750   0.8289   0.01931   0.01210  -0.0246   0.5394   0.9488
   5.000   0.8521   0.01927   0.01208  -0.0241   0.5364   0.9492
   5.250   0.8779   0.01889   0.01167  -0.0237   0.5330   0.9496
   5.500   0.9001   0.01891   0.01175  -0.0231   0.5295   0.9502
   5.750   0.9187   0.01917   0.01214  -0.0221   0.5246   0.9510
   6.000   0.9407   0.01912   0.01214  -0.0214   0.5208   0.9517
   6.250   0.9657   0.01879   0.01180  -0.0209   0.5170   0.9523
   6.500   0.9815   0.01913   0.01230  -0.0196   0.5111   0.9538
   6.750   1.0007   0.01904   0.01226  -0.0184   0.5043   0.9551
   7.000   1.0149   0.01911   0.01241  -0.0164   0.4975   0.9565
   7.250   1.0214   0.01933   0.01272  -0.0131   0.4906   0.9586
   7.500   1.0312   0.01945   0.01291  -0.0104   0.4837   0.9603
   7.750   1.0485   0.01981   0.01337  -0.0097   0.4740   0.9615
   8.000   1.0583   0.02057   0.01427  -0.0083   0.4637   0.9634
   8.250   1.0502   0.02182   0.01561  -0.0048   0.4534   0.9672
   8.500   1.0272   0.02378   0.01765   0.0002   0.4426   0.9733
   8.750   1.0431   0.02428   0.01802   0.0005   0.4000   0.9748
   9.000   1.0399   0.02584   0.01915   0.0024   0.3494   0.9778
   9.250   1.0311   0.02812   0.02129   0.0043   0.3275   0.9815
   9.500   1.0223   0.03047   0.02353   0.0062   0.3021   0.9850
   9.750   1.0083   0.03381   0.02661   0.0072   0.2366   0.9880
  10.000   0.9867   0.03777   0.03022   0.0086   0.1950   0.9917
  10.250   0.9831   0.04043   0.03275   0.0093   0.1629   0.9945
  10.500   0.9733   0.04396   0.03597   0.0096   0.1126   0.9976
  10.750   0.9767   0.04650   0.03840   0.0094   0.0962   0.9997
  11.000   0.9729   0.04804   0.03993   0.0119   0.0909   1.0000
  11.500   0.9647   0.05070   0.04260   0.0176   0.0845   1.0000
  11.750   0.9638   0.05220   0.04412   0.0196   0.0823   1.0000
  12.000   0.9649   0.05379   0.04572   0.0213   0.0801   1.0000
  12.250   0.9696   0.05522   0.04721   0.0225   0.0788   1.0000
  12.500   0.9747   0.05673   0.04879   0.0236   0.0775   1.0000
  12.750   0.9802   0.05827   0.05040   0.0246   0.0762   1.0000
  13.000   0.9862   0.05982   0.05202   0.0255   0.0751   1.0000
  13.250   0.9922   0.06142   0.05367   0.0262   0.0735   1.0000
  13.500   0.9977   0.06309   0.05538   0.0270   0.0721   1.0000
  13.750   1.0031   0.06479   0.05709   0.0276   0.0700   1.0000
  14.000   1.0077   0.06651   0.05880   0.0284   0.0677   1.0000
  14.250   1.0170   0.06793   0.06030   0.0288   0.0661   1.0000
  14.500   1.0258   0.06943   0.06191   0.0292   0.0641   1.0000
  14.750   1.0340   0.07101   0.06357   0.0295   0.0617   1.0000
  15.000   1.0414   0.07271   0.06532   0.0298   0.0593   1.0000
  15.250   1.0478   0.07450   0.06713   0.0300   0.0571   1.0000
  15.500   1.0541   0.07620   0.06884   0.0304   0.0548   1.0000
  15.750   1.0626   0.07797   0.07076   0.0304   0.0527   1.0000
  16.000   1.0711   0.07966   0.07257   0.0305   0.0509   1.0000
  16.250   1.0777   0.08167   0.07467   0.0303   0.0481   1.0000
  16.500   1.0824   0.08390   0.07695   0.0302   0.0458   1.0000
  16.750   1.0890   0.08593   0.07907   0.0300   0.0433   1.0000
  17.000   1.0964   0.08791   0.08120   0.0298   0.0398   1.0000
  17.250   1.1012   0.09031   0.08366   0.0293   0.0357   1.0000
  17.500   1.1078   0.09241   0.08586   0.0290   0.0315   1.0000
  17.750   1.1118   0.09486   0.08835   0.0286   0.0269   1.0000
  18.000   1.1145   0.09749   0.09100   0.0281   0.0235   1.0000
  18.250   1.1160   0.10030   0.09383   0.0276   0.0213   1.0000
  18.500   1.1164   0.10326   0.09682   0.0271   0.0199   1.0000
  18.750   1.1166   0.10627   0.09990   0.0265   0.0182   1.0000
  19.000   1.1150   0.10958   0.10327   0.0257   0.0171   1.0000
  19.250   1.1119   0.11319   0.10695   0.0248   0.0164   1.0000
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