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NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 63(2)-215 MOD B (n63215b-il)
Reynolds number: 50,000
Max Cl/Cd: 24.53 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63215b-il-50000-n5.txt
Download as CSV file: xf-n63215b-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)-215 MOD B                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5757   0.10346   0.09565  -0.0283   1.0000   0.0652
 -12.500  -0.6228   0.08968   0.08177  -0.0374   1.0000   0.0640
 -12.250  -0.6778   0.07796   0.06982  -0.0454   1.0000   0.0626
 -12.000  -0.7140   0.07081   0.06242  -0.0493   1.0000   0.0621
 -11.750  -0.7353   0.06596   0.05736  -0.0509   1.0000   0.0622
 -11.500  -0.7492   0.06209   0.05330  -0.0514   1.0000   0.0626
 -11.250  -0.7582   0.05882   0.04986  -0.0512   1.0000   0.0632
 -11.000  -0.7645   0.05599   0.04686  -0.0504   1.0000   0.0643
 -10.750  -0.7696   0.05344   0.04412  -0.0491   1.0000   0.0656
 -10.500  -0.7726   0.05101   0.04145  -0.0474   1.0000   0.0671
 -10.250  -0.7714   0.04856   0.03868  -0.0459   1.0000   0.0688
 -10.000  -0.7622   0.04625   0.03615  -0.0446   1.0000   0.0704
  -9.500  -0.7278   0.04276   0.03260  -0.0429   1.0000   0.0749
  -9.250  -0.7128   0.04119   0.03088  -0.0416   1.0000   0.0783
  -9.000  -0.6956   0.03966   0.02908  -0.0403   1.0000   0.0815
  -8.750  -0.6716   0.03830   0.02790  -0.0395   1.0000   0.0848
  -8.500  -0.6529   0.03718   0.02678  -0.0381   1.0000   0.0886
  -8.250  -0.6367   0.03619   0.02563  -0.0364   1.0000   0.0937
  -8.000  -0.6257   0.03524   0.02481  -0.0341   1.0000   0.0981
  -7.750  -0.6193   0.03442   0.02403  -0.0312   1.0000   0.1029
  -7.500  -0.6151   0.03370   0.02324  -0.0279   1.0000   0.1080
  -7.250  -0.6177   0.03293   0.02259  -0.0241   1.0000   0.1126
  -7.000  -0.6195   0.03221   0.02189  -0.0203   1.0000   0.1189
  -6.750  -0.6210   0.03141   0.02114  -0.0167   1.0000   0.1264
  -6.500  -0.6150   0.03044   0.02021  -0.0145   0.9978   0.1387
  -6.250  -0.5921   0.02885   0.01886  -0.0159   0.9875   0.1651
  -6.000  -0.5706   0.02709   0.01756  -0.0173   0.9780   0.2153
  -5.750  -0.5520   0.02557   0.01682  -0.0178   0.9682   0.3088
  -5.500  -0.5287   0.02528   0.01707  -0.0172   0.9595   0.4115
  -5.250  -0.4980   0.02564   0.01753  -0.0174   0.9524   0.4803
  -5.000  -0.4733   0.02613   0.01797  -0.0164   0.9437   0.5231
  -4.750  -0.4409   0.02677   0.01852  -0.0164   0.9375   0.5575
  -4.500  -0.4155   0.02745   0.01914  -0.0148   0.9297   0.5800
  -4.250  -0.3826   0.02812   0.01972  -0.0145   0.9238   0.6016
  -4.000  -0.3562   0.02860   0.02010  -0.0135   0.9169   0.6211
  -3.750  -0.3276   0.02900   0.02040  -0.0129   0.9104   0.6375
  -3.500  -0.2918   0.02928   0.02056  -0.0137   0.9060   0.6502
  -3.250  -0.2727   0.02924   0.02042  -0.0124   0.8975   0.6613
  -3.000  -0.2431   0.02912   0.02016  -0.0131   0.8918   0.6738
  -2.750  -0.2178   0.02932   0.02031  -0.0122   0.8853   0.6815
  -2.500  -0.1940   0.02919   0.02007  -0.0120   0.8784   0.6921
  -2.250  -0.1604   0.02924   0.02004  -0.0128   0.8738   0.6999
  -2.000  -0.1445   0.02916   0.01989  -0.0114   0.8653   0.7094
  -1.750  -0.1128   0.02917   0.01984  -0.0119   0.8593   0.7173
  -1.500  -0.0901   0.02907   0.01968  -0.0113   0.8497   0.7264
  -1.250  -0.0504   0.02890   0.01944  -0.0127   0.8411   0.7340
  -1.000  -0.0266   0.02869   0.01917  -0.0119   0.8281   0.7427
  -0.750   0.0020   0.02852   0.01897  -0.0114   0.8156   0.7501
  -0.500   0.0336   0.02821   0.01860  -0.0116   0.8045   0.7587
  -0.250   0.0643   0.02799   0.01836  -0.0113   0.7929   0.7660
   0.000   0.0886   0.02770   0.01804  -0.0102   0.7786   0.7752
   0.250   0.1157   0.02740   0.01773  -0.0091   0.7637   0.7830
   0.500   0.1409   0.02705   0.01737  -0.0080   0.7491   0.7921
   0.750   0.1672   0.02675   0.01708  -0.0068   0.7351   0.8002
   1.000   0.1927   0.02640   0.01672  -0.0057   0.7205   0.8091
   1.250   0.2181   0.02604   0.01638  -0.0044   0.7044   0.8176
   1.500   0.2417   0.02566   0.01601  -0.0029   0.6859   0.8266
   1.750   0.2650   0.02526   0.01563  -0.0012   0.6655   0.8362
   2.000   0.2907   0.02478   0.01514   0.0003   0.6427   0.8450
   2.250   0.3105   0.02443   0.01481   0.0023   0.6143   0.8562
   2.500   0.3341   0.02405   0.01443   0.0039   0.5794   0.8659
   2.750   0.3565   0.02374   0.01404   0.0056   0.5355   0.8766
   3.000   0.3796   0.02351   0.01359   0.0072   0.4822   0.8883
   3.250   0.4056   0.02353   0.01321   0.0082   0.4286   0.8988
   3.500   0.4295   0.02387   0.01313   0.0090   0.3912   0.9101
   3.750   0.4545   0.02437   0.01330   0.0091   0.3654   0.9223
   4.000   0.4828   0.02497   0.01367   0.0086   0.3446   0.9347
   4.250   0.5175   0.02562   0.01418   0.0068   0.3259   0.9455
   4.500   0.5543   0.02627   0.01474   0.0046   0.3098   0.9569
   4.750   0.5923   0.02692   0.01532   0.0021   0.2951   0.9689
   5.000   0.6318   0.02758   0.01592  -0.0006   0.2819   0.9813
   5.250   0.6726   0.02826   0.01652  -0.0037   0.2706   0.9945
   5.500   0.6896   0.02877   0.01709  -0.0027   0.2621   1.0000
   5.750   0.7020   0.02926   0.01748  -0.0007   0.2553   1.0000
   6.000   0.7180   0.02987   0.01812   0.0005   0.2475   1.0000
   6.250   0.7383   0.03051   0.01870   0.0011   0.2398   1.0000
   6.500   0.7605   0.03130   0.01949   0.0014   0.2326   1.0000
   6.750   0.7829   0.03209   0.02030   0.0016   0.2253   1.0000
   7.000   0.8074   0.03292   0.02104   0.0016   0.2193   1.0000
   7.250   0.8293   0.03397   0.02224   0.0018   0.2129   1.0000
   7.500   0.8537   0.03494   0.02320   0.0017   0.2077   1.0000
   7.750   0.8780   0.03602   0.02426   0.0017   0.2031   1.0000
   8.000   0.8962   0.03733   0.02580   0.0022   0.1972   1.0000
   8.250   0.9176   0.03837   0.02686   0.0025   0.1921   1.0000
   8.500   0.9404   0.03945   0.02789   0.0026   0.1877   1.0000
   8.750   0.9529   0.04115   0.02991   0.0035   0.1827   1.0000
   9.000   0.9695   0.04270   0.03160   0.0040   0.1788   1.0000
   9.250   0.9897   0.04398   0.03290   0.0043   0.1753   1.0000
   9.500   1.0081   0.04544   0.03438   0.0047   0.1720   1.0000
   9.750   1.0083   0.04785   0.03717   0.0063   0.1682   1.0000
  10.000   1.0113   0.04998   0.03951   0.0076   0.1646   1.0000
  10.250   1.0206   0.05163   0.04125   0.0086   0.1613   1.0000
  10.500   1.0385   0.05291   0.04252   0.0089   0.1586   1.0000
  10.750   1.0373   0.05534   0.04509   0.0104   0.1566   1.0000
  11.000   1.0058   0.05958   0.04968   0.0125   0.1550   1.0000
  11.250   0.9599   0.06574   0.05615   0.0127   0.1537   1.0000
  11.500   0.8130   0.08747   0.07833   0.0021   0.1526   1.0000
  11.750   0.7412   0.10586   0.09681  -0.0090   0.1482   1.0000
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