Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NPL 9627 AIRFOIL (npl9627-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.4 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-npl9627-il-1000000-n5.txt
Download as CSV file: xf-npl9627-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -1.1162   0.10722   0.10432  -0.0030   1.0000   0.0067
 -17.750  -1.1560   0.09608   0.09302  -0.0090   1.0000   0.0067
 -17.500  -1.1949   0.08558   0.08235  -0.0146   1.0000   0.0067
 -17.250  -1.2296   0.07605   0.07266  -0.0197   1.0000   0.0066
 -17.000  -1.2600   0.06734   0.06378  -0.0246   1.0000   0.0066
 -16.750  -1.2831   0.05972   0.05601  -0.0291   1.0000   0.0066
 -16.500  -1.3003   0.05297   0.04910  -0.0333   1.0000   0.0066
 -16.250  -1.3117   0.04737   0.04335  -0.0368   1.0000   0.0066
 -16.000  -1.3188   0.04279   0.03864  -0.0394   1.0000   0.0066
 -15.750  -1.3232   0.03903   0.03475  -0.0411   1.0000   0.0066
 -15.500  -1.3243   0.03603   0.03163  -0.0419   1.0000   0.0067
 -15.250  -1.3240   0.03352   0.02901  -0.0421   1.0000   0.0067
 -15.000  -1.3217   0.03143   0.02682  -0.0416   1.0000   0.0067
 -14.750  -1.3182   0.02966   0.02494  -0.0406   1.0000   0.0067
 -14.500  -1.3133   0.02815   0.02334  -0.0392   1.0000   0.0067
 -14.250  -1.3068   0.02685   0.02195  -0.0375   1.0000   0.0068
 -14.000  -1.2993   0.02572   0.02073  -0.0356   1.0000   0.0068
 -13.750  -1.2907   0.02472   0.01966  -0.0335   1.0000   0.0068
 -13.500  -1.2803   0.02384   0.01870  -0.0314   1.0000   0.0068
 -13.250  -1.2661   0.02299   0.01778  -0.0298   1.0000   0.0068
 -13.000  -1.2504   0.02219   0.01691  -0.0285   1.0000   0.0069
 -12.750  -1.2334   0.02144   0.01609  -0.0272   1.0000   0.0069
 -12.500  -1.2155   0.02072   0.01531  -0.0260   1.0000   0.0069
 -12.250  -1.1968   0.02005   0.01458  -0.0249   1.0000   0.0070
 -12.000  -1.1774   0.01941   0.01388  -0.0238   1.0000   0.0070
 -11.750  -1.1574   0.01881   0.01323  -0.0228   1.0000   0.0071
 -11.500  -1.1370   0.01823   0.01260  -0.0217   1.0000   0.0071
 -11.250  -1.1162   0.01768   0.01201  -0.0208   1.0000   0.0072
 -11.000  -1.0952   0.01717   0.01145  -0.0198   1.0000   0.0072
 -10.750  -1.0741   0.01667   0.01091  -0.0187   1.0000   0.0073
 -10.500  -1.0529   0.01621   0.01041  -0.0177   1.0000   0.0074
 -10.250  -1.0320   0.01577   0.00994  -0.0165   1.0000   0.0075
 -10.000  -1.0112   0.01535   0.00949  -0.0153   1.0000   0.0075
  -9.750  -0.9904   0.01495   0.00906  -0.0141   1.0000   0.0076
  -9.500  -0.9697   0.01458   0.00866  -0.0128   1.0000   0.0078
  -9.250  -0.9490   0.01422   0.00828  -0.0115   1.0000   0.0080
  -9.000  -0.9177   0.01382   0.00785  -0.0124   0.9980   0.0084
  -8.750  -0.8852   0.01343   0.00744  -0.0136   0.9955   0.0088
  -8.500  -0.8524   0.01307   0.00704  -0.0149   0.9933   0.0093
  -8.250  -0.8218   0.01274   0.00669  -0.0156   0.9908   0.0096
  -8.000  -0.7921   0.01244   0.00636  -0.0161   0.9872   0.0098
  -7.750  -0.7620   0.01211   0.00601  -0.0167   0.9838   0.0101
  -7.500  -0.7307   0.01176   0.00565  -0.0175   0.9805   0.0105
  -7.250  -0.7024   0.01146   0.00533  -0.0177   0.9748   0.0110
  -7.000  -0.6726   0.01117   0.00504  -0.0182   0.9694   0.0114
  -6.750  -0.6434   0.01091   0.00476  -0.0185   0.9633   0.0118
  -6.500  -0.6150   0.01067   0.00450  -0.0185   0.9544   0.0122
  -6.250  -0.5876   0.01044   0.00426  -0.0184   0.9426   0.0128
  -6.000  -0.5609   0.01022   0.00402  -0.0180   0.9288   0.0136
  -5.500  -0.5083   0.00985   0.00361  -0.0172   0.9001   0.0176
  -5.250  -0.4818   0.00971   0.00343  -0.0168   0.8840   0.0202
  -5.000  -0.4551   0.00957   0.00324  -0.0164   0.8672   0.0213
  -4.750  -0.4282   0.00945   0.00308  -0.0161   0.8508   0.0226
  -4.500  -0.4012   0.00935   0.00291  -0.0158   0.8338   0.0236
  -4.250  -0.3742   0.00924   0.00275  -0.0155   0.8155   0.0246
  -4.000  -0.3472   0.00915   0.00261  -0.0152   0.7962   0.0261
  -3.500  -0.2926   0.00899   0.00233  -0.0148   0.7593   0.0291
  -3.250  -0.2653   0.00892   0.00221  -0.0146   0.7381   0.0311
  -3.000  -0.2382   0.00886   0.00209  -0.0143   0.7127   0.0345
  -2.750  -0.2112   0.00878   0.00196  -0.0141   0.6891   0.0437
  -2.250  -0.1599   0.00803   0.00158  -0.0134   0.6527   0.1635
  -2.000  -0.1338   0.00775   0.00146  -0.0131   0.6343   0.2174
  -1.750  -0.1071   0.00760   0.00138  -0.0129   0.6132   0.2554
  -1.500  -0.0799   0.00750   0.00132  -0.0127   0.5928   0.2862
  -1.250  -0.0524   0.00742   0.00128  -0.0126   0.5774   0.3121
  -1.000  -0.0249   0.00735   0.00125  -0.0125   0.5601   0.3387
  -0.750   0.0026   0.00734   0.00123  -0.0124   0.5375   0.3628
  -0.500   0.0302   0.00731   0.00121  -0.0123   0.5198   0.3863
  -0.250   0.0580   0.00726   0.00120  -0.0123   0.5070   0.4090
   0.000   0.0855   0.00716   0.00119  -0.0122   0.4944   0.4443
   0.250   0.1128   0.00706   0.00118  -0.0120   0.4804   0.4826
   0.500   0.1397   0.00697   0.00118  -0.0118   0.4609   0.5273
   0.750   0.1660   0.00692   0.00119  -0.0115   0.4320   0.5795
   1.000   0.1923   0.00692   0.00122  -0.0112   0.4040   0.6255
   1.250   0.2191   0.00690   0.00126  -0.0110   0.3834   0.6679
   1.500   0.2458   0.00690   0.00132  -0.0107   0.3610   0.7063
   1.750   0.2721   0.00697   0.00139  -0.0104   0.3340   0.7411
   2.000   0.2984   0.00706   0.00147  -0.0100   0.3059   0.7726
   2.250   0.3248   0.00716   0.00157  -0.0096   0.2825   0.8004
   2.500   0.3512   0.00729   0.00168  -0.0093   0.2568   0.8249
   2.750   0.3774   0.00747   0.00180  -0.0089   0.2303   0.8474
   3.000   0.4033   0.00766   0.00194  -0.0084   0.2028   0.8675
   3.250   0.4292   0.00789   0.00209  -0.0080   0.1735   0.8857
   3.500   0.4546   0.00819   0.00228  -0.0075   0.1413   0.9024
   4.000   0.5054   0.00881   0.00270  -0.0064   0.0854   0.9331
   4.250   0.5325   0.00901   0.00288  -0.0062   0.0779   0.9467
   4.500   0.5609   0.00920   0.00305  -0.0063   0.0738   0.9573
   4.750   0.5897   0.00940   0.00323  -0.0064   0.0704   0.9674
   5.000   0.6216   0.00958   0.00341  -0.0073   0.0689   0.9746
   5.250   0.6510   0.00976   0.00358  -0.0076   0.0672   0.9807
   5.500   0.6837   0.00997   0.00378  -0.0087   0.0650   0.9840
   5.750   0.7155   0.01022   0.00400  -0.0097   0.0624   0.9878
   6.000   0.7470   0.01041   0.00419  -0.0106   0.0613   0.9910
   6.250   0.7786   0.01060   0.00438  -0.0115   0.0599   0.9931
   6.500   0.8116   0.01081   0.00459  -0.0127   0.0585   0.9948
   6.750   0.8445   0.01104   0.00481  -0.0139   0.0570   0.9968
   7.000   0.8767   0.01129   0.00506  -0.0150   0.0554   0.9988
   7.250   0.9067   0.01153   0.00530  -0.0156   0.0542   1.0000
   7.500   0.9293   0.01171   0.00550  -0.0146   0.0533   1.0000
   7.750   0.9521   0.01191   0.00571  -0.0137   0.0519   1.0000
   8.000   0.9748   0.01212   0.00592  -0.0127   0.0503   1.0000
   8.250   0.9975   0.01237   0.00616  -0.0118   0.0486   1.0000
   8.500   1.0205   0.01260   0.00640  -0.0109   0.0471   1.0000
   8.750   1.0436   0.01283   0.00665  -0.0101   0.0450   1.0000
   9.000   1.0667   0.01311   0.00690  -0.0093   0.0423   1.0000
   9.250   1.0900   0.01339   0.00718  -0.0085   0.0390   1.0000
   9.500   1.1130   0.01372   0.00749  -0.0078   0.0362   1.0000
   9.750   1.1360   0.01407   0.00783  -0.0071   0.0341   1.0000
  10.000   1.1587   0.01443   0.00820  -0.0063   0.0324   1.0000
  10.250   1.1816   0.01480   0.00858  -0.0056   0.0310   1.0000
  10.500   1.2039   0.01520   0.00899  -0.0049   0.0298   1.0000
  10.750   1.2258   0.01563   0.00944  -0.0041   0.0286   1.0000
  11.000   1.2482   0.01602   0.00986  -0.0033   0.0278   1.0000
  11.250   1.2700   0.01644   0.01031  -0.0025   0.0270   1.0000
  11.500   1.2912   0.01690   0.01079  -0.0017   0.0263   1.0000
  11.750   1.3118   0.01738   0.01130  -0.0008   0.0257   1.0000
  12.000   1.3316   0.01791   0.01185   0.0002   0.0250   1.0000
  12.250   1.3517   0.01838   0.01237   0.0012   0.0246   1.0000
  12.500   1.3713   0.01886   0.01290   0.0022   0.0242   1.0000
  12.750   1.3900   0.01938   0.01347   0.0033   0.0238   1.0000
  13.000   1.4069   0.01993   0.01406   0.0047   0.0233   1.0000
  13.250   1.4215   0.02051   0.01469   0.0065   0.0228   1.0000
  13.500   1.4352   0.02117   0.01539   0.0082   0.0223   1.0000
  13.750   1.4480   0.02191   0.01618   0.0099   0.0219   1.0000
  14.000   1.4597   0.02275   0.01707   0.0116   0.0215   1.0000
  14.250   1.4731   0.02351   0.01790   0.0130   0.0212   1.0000
  14.500   1.4856   0.02437   0.01883   0.0143   0.0208   1.0000
  14.750   1.4971   0.02533   0.01986   0.0155   0.0204   1.0000
  15.000   1.5079   0.02641   0.02101   0.0167   0.0200   1.0000
  15.250   1.5175   0.02763   0.02229   0.0177   0.0196   1.0000
  15.500   1.5261   0.02901   0.02373   0.0185   0.0191   1.0000
  15.750   1.5335   0.03057   0.02536   0.0192   0.0187   1.0000
  16.000   1.5396   0.03234   0.02721   0.0197   0.0183   1.0000
  16.250   1.5462   0.03416   0.02911   0.0200   0.0181   1.0000
  16.500   1.5515   0.03619   0.03123   0.0200   0.0177   1.0000
  16.750   1.5555   0.03846   0.03359   0.0199   0.0173   1.0000
  17.000   1.5579   0.04098   0.03620   0.0196   0.0169   1.0000
  17.250   1.5585   0.04380   0.03910   0.0190   0.0166   1.0000
  17.500   1.5573   0.04691   0.04230   0.0183   0.0162   1.0000
  17.750   1.5538   0.05039   0.04587   0.0173   0.0159   1.0000
  18.000   1.5478   0.05424   0.04982   0.0160   0.0156   1.0000
  18.250   1.5408   0.05835   0.05404   0.0146   0.0154   1.0000
  18.500   1.5312   0.06288   0.05868   0.0129   0.0152   1.0000
  18.750   1.5196   0.06783   0.06375   0.0110   0.0150   1.0000
  19.000   1.5060   0.07319   0.06922   0.0087   0.0148   1.0000
  19.250   1.4893   0.07913   0.07528   0.0061   0.0147   1.0000
<< Back to NPL 9627 AIRFOIL (npl9627-il)

Polar data table (+)

Polar graphs


<< Back to NPL 9627 AIRFOIL (npl9627-il)