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NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NPL 9627 AIRFOIL (npl9627-il)
Reynolds number: 100,000
Max Cl/Cd: 42.32 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-npl9627-il-100000.txt
Download as CSV file: xf-npl9627-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6996   0.07782   0.07254  -0.0353   1.0000   0.0839
 -10.000  -0.5156   0.08564   0.08070  -0.0240   1.0000   0.1019
  -9.750  -0.8017   0.05979   0.05364  -0.0361   1.0000   0.0671
  -9.500  -0.8040   0.05569   0.04926  -0.0346   1.0000   0.0656
  -9.250  -0.8044   0.05171   0.04501  -0.0329   1.0000   0.0652
  -9.000  -0.8042   0.04792   0.04085  -0.0308   1.0000   0.0649
  -8.750  -0.8011   0.04440   0.03689  -0.0285   1.0000   0.0649
  -8.500  -0.7940   0.04122   0.03326  -0.0261   1.0000   0.0652
  -8.250  -0.7852   0.03854   0.03005  -0.0236   1.0000   0.0660
  -8.000  -0.7699   0.03584   0.02719  -0.0221   1.0000   0.0679
  -7.750  -0.7513   0.03392   0.02521  -0.0208   1.0000   0.0703
  -7.500  -0.7345   0.03205   0.02302  -0.0190   1.0000   0.0728
  -7.250  -0.7165   0.03023   0.02079  -0.0170   1.0000   0.0746
  -7.000  -0.6946   0.02804   0.01853  -0.0159   1.0000   0.0764
  -6.750  -0.6725   0.02644   0.01692  -0.0147   1.0000   0.0792
  -6.500  -0.6506   0.02506   0.01542  -0.0134   1.0000   0.0828
  -6.250  -0.6292   0.02361   0.01402  -0.0121   1.0000   0.0869
  -6.000  -0.6091   0.02260   0.01303  -0.0106   1.0000   0.0932
  -5.750  -0.5903   0.02154   0.01209  -0.0091   1.0000   0.1012
  -5.500  -0.5719   0.02060   0.01123  -0.0074   1.0000   0.1114
  -5.250  -0.5539   0.01964   0.01037  -0.0056   1.0000   0.1231
  -5.000  -0.5366   0.01862   0.00953  -0.0037   1.0000   0.1445
  -4.750  -0.5240   0.01683   0.00860  -0.0014   1.0000   0.2475
  -4.500  -0.5079   0.01627   0.00843   0.0005   1.0000   0.3481
  -4.250  -0.4889   0.01606   0.00829   0.0021   1.0000   0.3954
  -4.000  -0.4689   0.01582   0.00811   0.0035   1.0000   0.4318
  -3.750  -0.4488   0.01557   0.00797   0.0048   1.0000   0.4676
  -3.500  -0.4291   0.01532   0.00790   0.0062   1.0000   0.5093
  -3.250  -0.4095   0.01509   0.00791   0.0078   1.0000   0.5552
  -3.000  -0.3897   0.01490   0.00796   0.0093   1.0000   0.6027
  -2.750  -0.3697   0.01475   0.00803   0.0108   1.0000   0.6510
  -2.500  -0.3501   0.01466   0.00818   0.0126   1.0000   0.7002
  -2.250  -0.3313   0.01467   0.00840   0.0146   1.0000   0.7559
  -2.000  -0.3136   0.01486   0.00878   0.0171   1.0000   0.8173
  -1.750  -0.2733   0.01534   0.00932   0.0157   0.9938   0.8841
  -1.500  -0.2101   0.01596   0.00983   0.0098   0.9863   0.9348
  -1.250  -0.1278   0.01653   0.01023  -0.0004   0.9828   0.9647
  -1.000  -0.0360   0.01680   0.01034  -0.0128   0.9805   0.9832
  -0.750   0.0525   0.01672   0.01016  -0.0250   0.9745   0.9983
  -0.500   0.1195   0.01642   0.00979  -0.0334   0.9617   1.0000
  -0.250   0.1787   0.01606   0.00937  -0.0399   0.9461   1.0000
   0.000   0.2282   0.01569   0.00897  -0.0444   0.9269   1.0000
   0.250   0.2688   0.01534   0.00857  -0.0467   0.9054   1.0000
   0.500   0.2999   0.01505   0.00823  -0.0469   0.8824   1.0000
   0.750   0.3230   0.01488   0.00802  -0.0457   0.8570   1.0000
   1.000   0.3457   0.01474   0.00780  -0.0442   0.8343   1.0000
   1.250   0.3678   0.01465   0.00763  -0.0426   0.8131   1.0000
   1.500   0.3889   0.01466   0.00759  -0.0410   0.7902   1.0000
   1.750   0.4103   0.01470   0.00755  -0.0394   0.7686   1.0000
   2.000   0.4319   0.01473   0.00752  -0.0378   0.7470   1.0000
   2.250   0.4536   0.01478   0.00746  -0.0361   0.7254   1.0000
   2.500   0.4749   0.01486   0.00745  -0.0344   0.7017   1.0000
   2.750   0.4960   0.01493   0.00744  -0.0327   0.6767   1.0000
   3.000   0.5176   0.01501   0.00739  -0.0309   0.6524   1.0000
   3.250   0.5386   0.01513   0.00744  -0.0293   0.6261   1.0000
   3.500   0.5599   0.01524   0.00742  -0.0275   0.6003   1.0000
   3.750   0.5808   0.01537   0.00750  -0.0259   0.5731   1.0000
   4.000   0.6022   0.01554   0.00758  -0.0244   0.5481   1.0000
   4.250   0.6237   0.01575   0.00772  -0.0229   0.5243   1.0000
   4.500   0.6448   0.01596   0.00790  -0.0214   0.4979   1.0000
   4.750   0.6655   0.01618   0.00805  -0.0199   0.4707   1.0000
   5.000   0.6856   0.01641   0.00820  -0.0182   0.4403   1.0000
   5.250   0.7049   0.01670   0.00840  -0.0164   0.4055   1.0000
   5.500   0.7229   0.01708   0.00867  -0.0145   0.3611   1.0000
   5.750   0.7373   0.01781   0.00903  -0.0121   0.3018   1.0000
   6.000   0.7500   0.01898   0.00976  -0.0096   0.2396   1.0000
   6.250   0.7662   0.02010   0.01057  -0.0076   0.2075   1.0000
   6.500   0.7851   0.02107   0.01139  -0.0061   0.1902   1.0000
   6.750   0.8056   0.02202   0.01224  -0.0048   0.1780   1.0000
   7.000   0.8267   0.02303   0.01311  -0.0037   0.1685   1.0000
   7.250   0.8485   0.02391   0.01401  -0.0027   0.1597   1.0000
   7.500   0.8707   0.02500   0.01506  -0.0019   0.1521   1.0000
   7.750   0.8928   0.02595   0.01602  -0.0010   0.1448   1.0000
   8.000   0.9159   0.02727   0.01730  -0.0004   0.1387   1.0000
   8.250   0.9375   0.02835   0.01853   0.0006   0.1327   1.0000
   8.500   0.9620   0.02991   0.01991   0.0008   0.1272   1.0000
   8.750   0.9817   0.03123   0.02155   0.0021   0.1226   1.0000
   9.000   1.0027   0.03270   0.02318   0.0031   0.1183   1.0000
   9.250   1.0262   0.03458   0.02496   0.0033   0.1144   1.0000
   9.500   1.0416   0.03652   0.02730   0.0049   0.1112   1.0000
   9.750   1.0566   0.03842   0.02953   0.0065   0.1080   1.0000
  10.000   1.0733   0.04047   0.03177   0.0077   0.1055   1.0000
  10.250   1.0911   0.04267   0.03407   0.0085   0.1033   1.0000
  10.500   1.1051   0.04594   0.03747   0.0094   0.1013   1.0000
  10.750   1.1051   0.04864   0.04070   0.0122   0.1001   1.0000
  11.000   1.1016   0.05184   0.04436   0.0148   0.0991   1.0000
  11.250   1.0937   0.05546   0.04838   0.0173   0.0986   1.0000
  11.500   1.0795   0.05938   0.05265   0.0199   0.0985   1.0000
  11.750   1.0578   0.06338   0.05693   0.0226   0.0986   1.0000
  12.000   1.0304   0.06783   0.06160   0.0244   0.0991   1.0000
  12.250   1.0003   0.07326   0.06722   0.0243   0.0997   1.0000
  12.500   0.9710   0.07975   0.07386   0.0223   0.1005   1.0000
  12.750   0.9480   0.08684   0.08104   0.0196   0.1012   1.0000
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