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NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NPL 9627 AIRFOIL (npl9627-il)
Reynolds number: 100,000
Max Cl/Cd: 40.15 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-npl9627-il-100000-n5.txt
Download as CSV file: xf-npl9627-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL 9627 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7367   0.09028   0.08455  -0.0211   1.0000   0.0272
 -12.250  -0.7624   0.08066   0.07481  -0.0283   1.0000   0.0269
 -12.000  -0.7883   0.07215   0.06612  -0.0350   1.0000   0.0267
 -11.750  -0.8121   0.06542   0.05917  -0.0397   1.0000   0.0265
 -11.500  -0.8334   0.06020   0.05371  -0.0421   1.0000   0.0265
 -11.250  -0.8525   0.05603   0.04929  -0.0422   1.0000   0.0265
 -11.000  -0.8693   0.05258   0.04555  -0.0405   1.0000   0.0267
 -10.750  -0.8827   0.04934   0.04193  -0.0380   1.0000   0.0270
 -10.500  -0.8863   0.04646   0.03872  -0.0359   1.0000   0.0275
 -10.250  -0.8765   0.04473   0.03694  -0.0346   1.0000   0.0281
 -10.000  -0.8681   0.04280   0.03485  -0.0331   1.0000   0.0290
  -9.750  -0.8606   0.04059   0.03232  -0.0313   1.0000   0.0300
  -9.500  -0.8531   0.03816   0.02939  -0.0292   1.0000   0.0312
  -9.250  -0.8375   0.03665   0.02785  -0.0281   1.0000   0.0323
  -9.000  -0.8218   0.03520   0.02627  -0.0268   1.0000   0.0338
  -8.750  -0.8071   0.03346   0.02413  -0.0251   1.0000   0.0356
  -8.500  -0.7890   0.03211   0.02282  -0.0241   1.0000   0.0371
  -8.250  -0.7708   0.03078   0.02135  -0.0228   1.0000   0.0389
  -8.000  -0.7518   0.02933   0.01965  -0.0214   1.0000   0.0404
  -7.750  -0.7328   0.02797   0.01833  -0.0201   1.0000   0.0417
  -7.500  -0.7142   0.02680   0.01713  -0.0187   1.0000   0.0432
  -7.250  -0.6957   0.02570   0.01595  -0.0172   1.0000   0.0450
  -7.000  -0.6782   0.02465   0.01488  -0.0155   1.0000   0.0468
  -6.750  -0.6611   0.02372   0.01396  -0.0138   1.0000   0.0490
  -6.500  -0.6430   0.02293   0.01306  -0.0121   1.0000   0.0520
  -6.250  -0.6261   0.02209   0.01227  -0.0105   1.0000   0.0555
  -6.000  -0.6082   0.02136   0.01152  -0.0089   1.0000   0.0604
  -5.750  -0.5900   0.02069   0.01081  -0.0073   1.0000   0.0660
  -5.500  -0.5722   0.01995   0.01010  -0.0057   1.0000   0.0715
  -5.250  -0.5537   0.01925   0.00943  -0.0042   1.0000   0.0794
  -5.000  -0.5351   0.01852   0.00880  -0.0027   1.0000   0.0936
  -4.750  -0.5169   0.01768   0.00822  -0.0013   1.0000   0.1313
  -4.500  -0.4984   0.01692   0.00781  -0.0001   1.0000   0.1960
  -4.250  -0.4789   0.01642   0.00757   0.0011   1.0000   0.2500
  -4.000  -0.4517   0.01607   0.00736   0.0008   0.9971   0.2969
  -3.750  -0.4145   0.01571   0.00722  -0.0015   0.9897   0.3537
  -3.500  -0.3774   0.01539   0.00709  -0.0037   0.9817   0.4114
  -3.250  -0.3421   0.01503   0.00693  -0.0053   0.9725   0.4594
  -3.000  -0.3042   0.01471   0.00675  -0.0074   0.9642   0.4989
  -2.750  -0.2674   0.01442   0.00657  -0.0091   0.9544   0.5331
  -2.500  -0.2325   0.01413   0.00643  -0.0103   0.9437   0.5724
  -2.250  -0.1964   0.01386   0.00631  -0.0116   0.9341   0.6186
  -2.000  -0.1642   0.01364   0.00625  -0.0119   0.9216   0.6679
  -1.750  -0.1320   0.01348   0.00624  -0.0121   0.9088   0.7171
  -1.500  -0.0981   0.01339   0.00623  -0.0125   0.8964   0.7631
  -1.250  -0.0624   0.01334   0.00624  -0.0131   0.8841   0.8033
  -1.000  -0.0284   0.01335   0.00625  -0.0135   0.8686   0.8366
  -0.750   0.0058   0.01338   0.00624  -0.0140   0.8524   0.8652
  -0.500   0.0425   0.01341   0.00622  -0.0149   0.8349   0.8877
  -0.250   0.0789   0.01345   0.00617  -0.0159   0.8161   0.9072
   0.000   0.1151   0.01349   0.00612  -0.0169   0.7966   0.9241
   0.250   0.1515   0.01354   0.00608  -0.0181   0.7768   0.9391
   0.500   0.1883   0.01360   0.00604  -0.0195   0.7557   0.9526
   0.750   0.2284   0.01366   0.00600  -0.0216   0.7335   0.9638
   1.000   0.2687   0.01370   0.00593  -0.0239   0.7113   0.9736
   1.250   0.3076   0.01375   0.00588  -0.0260   0.6899   0.9834
   1.500   0.3465   0.01381   0.00584  -0.0282   0.6696   0.9926
   1.750   0.3859   0.01385   0.00582  -0.0306   0.6487   1.0000
   2.000   0.4089   0.01393   0.00582  -0.0297   0.6295   1.0000
   2.250   0.4317   0.01403   0.00584  -0.0287   0.6088   1.0000
   2.500   0.4542   0.01415   0.00587  -0.0276   0.5866   1.0000
   2.750   0.4764   0.01429   0.00589  -0.0265   0.5630   1.0000
   3.000   0.4983   0.01444   0.00597  -0.0253   0.5364   1.0000
   3.250   0.5200   0.01463   0.00603  -0.0241   0.5102   1.0000
   3.500   0.5416   0.01482   0.00613  -0.0228   0.4814   1.0000
   3.750   0.5628   0.01505   0.00623  -0.0216   0.4506   1.0000
   4.000   0.5839   0.01531   0.00638  -0.0203   0.4213   1.0000
   4.250   0.6055   0.01557   0.00658  -0.0191   0.3954   1.0000
   4.500   0.6267   0.01589   0.00679  -0.0179   0.3682   1.0000
   4.750   0.6475   0.01624   0.00705  -0.0167   0.3382   1.0000
   5.000   0.6678   0.01665   0.00733  -0.0154   0.3068   1.0000
   5.250   0.6877   0.01713   0.00767  -0.0140   0.2735   1.0000
   5.500   0.7069   0.01768   0.00808  -0.0126   0.2392   1.0000
   5.750   0.7257   0.01831   0.00854  -0.0112   0.2040   1.0000
   6.000   0.7439   0.01903   0.00908  -0.0097   0.1721   1.0000
   6.250   0.7622   0.01976   0.00968  -0.0083   0.1506   1.0000
   6.500   0.7808   0.02049   0.01033  -0.0069   0.1370   1.0000
   6.750   0.7993   0.02123   0.01101  -0.0055   0.1281   1.0000
   7.000   0.8186   0.02191   0.01170  -0.0041   0.1211   1.0000
   7.250   0.8370   0.02266   0.01243  -0.0028   0.1152   1.0000
   7.500   0.8560   0.02339   0.01319  -0.0015   0.1100   1.0000
   7.750   0.8750   0.02413   0.01394  -0.0002   0.1049   1.0000
   8.000   0.8928   0.02499   0.01477   0.0011   0.1006   1.0000
   8.250   0.9122   0.02574   0.01561   0.0022   0.0963   1.0000
   8.500   0.9305   0.02659   0.01646   0.0034   0.0925   1.0000
   8.750   0.9484   0.02756   0.01743   0.0046   0.0893   1.0000
   9.000   0.9675   0.02845   0.01845   0.0058   0.0859   1.0000
   9.250   0.9857   0.02941   0.01944   0.0069   0.0828   1.0000
   9.500   1.0035   0.03053   0.02051   0.0079   0.0802   1.0000
   9.750   1.0220   0.03165   0.02180   0.0090   0.0777   1.0000
  10.000   1.0399   0.03281   0.02309   0.0101   0.0751   1.0000
  10.250   1.0572   0.03397   0.02431   0.0112   0.0727   1.0000
  10.500   1.0761   0.03531   0.02557   0.0119   0.0706   1.0000
  10.750   1.0901   0.03672   0.02726   0.0133   0.0684   1.0000
  11.000   1.1043   0.03821   0.02896   0.0146   0.0664   1.0000
  11.250   1.1183   0.03971   0.03060   0.0158   0.0647   1.0000
  11.500   1.1326   0.04118   0.03212   0.0169   0.0633   1.0000
  11.750   1.1478   0.04284   0.03380   0.0178   0.0619   1.0000
  12.000   1.1483   0.04479   0.03611   0.0203   0.0605   1.0000
  12.250   1.1486   0.04683   0.03843   0.0225   0.0592   1.0000
  12.500   1.1486   0.04896   0.04079   0.0243   0.0581   1.0000
  12.750   1.1483   0.05119   0.04321   0.0258   0.0571   1.0000
  13.000   1.1487   0.05342   0.04559   0.0268   0.0562   1.0000
  13.250   1.1507   0.05561   0.04787   0.0276   0.0554   1.0000
  13.500   1.1539   0.05790   0.05021   0.0281   0.0546   1.0000
  13.750   1.1334   0.06222   0.05489   0.0280   0.0541   1.0000
  14.000   1.1105   0.06735   0.06034   0.0267   0.0537   1.0000
  14.250   1.0841   0.07353   0.06682   0.0240   0.0534   1.0000
  14.500   1.0520   0.08124   0.07482   0.0198   0.0533   1.0000
  14.750   1.0104   0.09152   0.08536   0.0133   0.0535   1.0000
  15.000   0.9448   0.10819   0.10229   0.0020   0.0541   1.0000
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