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

NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NPL 9510 AIRFOIL (npl9510-il)
Reynolds number: 1,000,000
Max Cl/Cd: 67.85 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-npl9510-il-1000000-n5.txt
Download as CSV file: xf-npl9510-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL 9510 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.1789   0.12410   0.12100  -0.0096   1.0000   0.0126
 -19.500  -1.1973   0.11685   0.11365  -0.0133   1.0000   0.0127
 -19.250  -1.2156   0.10976   0.10646  -0.0169   1.0000   0.0127
 -19.000  -1.2325   0.10302   0.09961  -0.0203   1.0000   0.0128
 -18.750  -1.2491   0.09648   0.09296  -0.0235   1.0000   0.0128
 -18.500  -1.2633   0.09048   0.08686  -0.0264   1.0000   0.0129
 -18.250  -1.2759   0.08481   0.08109  -0.0291   1.0000   0.0129
 -18.000  -1.2870   0.07951   0.07568  -0.0316   1.0000   0.0130
 -17.750  -1.2962   0.07459   0.07067  -0.0339   1.0000   0.0131
 -17.500  -1.3034   0.07008   0.06607  -0.0359   1.0000   0.0132
 -17.250  -1.3092   0.06588   0.06177  -0.0378   1.0000   0.0133
 -17.000  -1.3131   0.06198   0.05779  -0.0395   1.0000   0.0134
 -16.750  -1.3156   0.05838   0.05410  -0.0410   1.0000   0.0135
 -16.500  -1.3171   0.05500   0.05064  -0.0423   1.0000   0.0136
 -16.250  -1.3175   0.05182   0.04738  -0.0435   1.0000   0.0137
 -16.000  -1.3173   0.04884   0.04432  -0.0446   1.0000   0.0138
 -15.750  -1.3166   0.04604   0.04144  -0.0455   1.0000   0.0140
 -15.500  -1.3148   0.04343   0.03876  -0.0463   1.0000   0.0141
 -15.250  -1.3117   0.04098   0.03624  -0.0470   1.0000   0.0142
 -15.000  -1.3074   0.03870   0.03388  -0.0476   1.0000   0.0144
 -14.750  -1.3018   0.03656   0.03167  -0.0482   1.0000   0.0146
 -14.500  -1.2948   0.03459   0.02963  -0.0487   1.0000   0.0147
 -14.250  -1.2868   0.03276   0.02773  -0.0491   1.0000   0.0148
 -14.000  -1.2781   0.03102   0.02592  -0.0495   1.0000   0.0150
 -13.750  -1.2732   0.02895   0.02379  -0.0498   1.0000   0.0152
 -13.500  -1.2680   0.02710   0.02189  -0.0498   1.0000   0.0154
 -13.250  -1.2650   0.02547   0.02021  -0.0490   1.0000   0.0156
 -13.000  -1.2561   0.02399   0.01868  -0.0490   1.0000   0.0159
 -12.750  -1.2440   0.02266   0.01731  -0.0492   1.0000   0.0161
 -12.500  -1.2289   0.02146   0.01606  -0.0497   1.0000   0.0164
 -12.250  -1.2115   0.02042   0.01496  -0.0502   1.0000   0.0167
 -12.000  -1.1870   0.01956   0.01404  -0.0515   0.9995   0.0170
 -11.750  -1.1585   0.01878   0.01321  -0.0532   0.9985   0.0173
 -11.500  -1.1296   0.01807   0.01246  -0.0548   0.9976   0.0177
 -11.250  -1.1000   0.01743   0.01176  -0.0564   0.9966   0.0180
 -11.000  -1.0702   0.01675   0.01104  -0.0580   0.9957   0.0184
 -10.750  -1.0401   0.01611   0.01039  -0.0596   0.9950   0.0190
 -10.500  -1.0098   0.01556   0.00981  -0.0611   0.9944   0.0197
 -10.250  -0.9797   0.01506   0.00929  -0.0624   0.9937   0.0203
 -10.000  -0.9504   0.01461   0.00880  -0.0635   0.9925   0.0210
  -9.750  -0.9203   0.01418   0.00834  -0.0646   0.9913   0.0217
  -9.500  -0.8897   0.01369   0.00785  -0.0659   0.9902   0.0229
  -9.250  -0.8587   0.01328   0.00743  -0.0672   0.9892   0.0243
  -9.000  -0.8274   0.01291   0.00704  -0.0685   0.9883   0.0254
  -8.750  -0.7959   0.01250   0.00663  -0.0698   0.9875   0.0272
  -8.500  -0.7644   0.01213   0.00626  -0.0711   0.9868   0.0291
  -8.250  -0.7328   0.01178   0.00591  -0.0724   0.9860   0.0312
  -8.000  -0.7012   0.01144   0.00558  -0.0736   0.9853   0.0342
  -7.750  -0.6695   0.01110   0.00525  -0.0749   0.9846   0.0377
  -7.500  -0.6377   0.01077   0.00494  -0.0761   0.9839   0.0426
  -7.250  -0.6079   0.01043   0.00464  -0.0770   0.9823   0.0493
  -7.000  -0.5779   0.01007   0.00434  -0.0778   0.9805   0.0590
  -6.750  -0.5474   0.00973   0.00406  -0.0788   0.9789   0.0706
  -6.500  -0.5165   0.00942   0.00381  -0.0797   0.9773   0.0836
  -6.250  -0.4855   0.00913   0.00358  -0.0807   0.9757   0.0960
  -6.000  -0.4545   0.00887   0.00337  -0.0816   0.9743   0.1076
  -5.750  -0.4233   0.00861   0.00317  -0.0826   0.9730   0.1204
  -5.500  -0.3920   0.00836   0.00298  -0.0835   0.9718   0.1352
  -5.250  -0.3623   0.00810   0.00280  -0.0841   0.9697   0.1537
  -4.750  -0.3025   0.00755   0.00244  -0.0854   0.9649   0.1976
  -4.500  -0.2715   0.00704   0.00218  -0.0866   0.9629   0.2557
  -4.250  -0.2404   0.00659   0.00196  -0.0877   0.9610   0.3143
  -4.000  -0.2097   0.00632   0.00183  -0.0884   0.9593   0.3511
  -3.750  -0.1794   0.00614   0.00175  -0.0890   0.9574   0.3792
  -3.500  -0.1499   0.00604   0.00170  -0.0894   0.9547   0.3946
  -3.250  -0.1204   0.00596   0.00165  -0.0897   0.9520   0.4068
  -3.000  -0.0908   0.00589   0.00162  -0.0900   0.9495   0.4172
  -2.750  -0.0611   0.00583   0.00159  -0.0903   0.9472   0.4278
  -2.500  -0.0314   0.00578   0.00157  -0.0906   0.9451   0.4368
  -2.250  -0.0021   0.00573   0.00154  -0.0907   0.9416   0.4442
  -2.000   0.0260   0.00566   0.00150  -0.0905   0.9329   0.4562
  -1.750   0.0527   0.00558   0.00143  -0.0899   0.9141   0.4684
  -1.500   0.0790   0.00559   0.00134  -0.0891   0.8819   0.4767
  -1.250   0.1067   0.00564   0.00132  -0.0888   0.8515   0.4846
  -1.000   0.1330   0.00584   0.00129  -0.0881   0.7897   0.4898
  -0.750   0.1443   0.00832   0.00170  -0.0855   0.2278   0.4937
  -0.500   0.1717   0.00868   0.00179  -0.0854   0.1450   0.4977
  -0.250   0.1996   0.00893   0.00187  -0.0854   0.0941   0.5017
   0.000   0.2279   0.00914   0.00195  -0.0854   0.0640   0.5051
   0.250   0.2564   0.00928   0.00203  -0.0855   0.0512   0.5085
   0.500   0.2851   0.00940   0.00213  -0.0855   0.0441   0.5122
   0.750   0.3137   0.00952   0.00222  -0.0856   0.0400   0.5159
   1.000   0.3423   0.00965   0.00233  -0.0856   0.0371   0.5195
   1.250   0.3708   0.00978   0.00244  -0.0856   0.0350   0.5226
   1.500   0.3993   0.00992   0.00257  -0.0856   0.0331   0.5260
   1.750   0.4277   0.01005   0.00271  -0.0855   0.0317   0.5296
   2.000   0.4561   0.01019   0.00285  -0.0855   0.0304   0.5331
   2.250   0.4844   0.01035   0.00300  -0.0855   0.0293   0.5363
   2.500   0.5124   0.01054   0.00318  -0.0854   0.0282   0.5393
   2.750   0.5405   0.01071   0.00336  -0.0853   0.0273   0.5426
   3.000   0.5687   0.01087   0.00354  -0.0852   0.0265   0.5460
   3.250   0.5967   0.01105   0.00373  -0.0851   0.0257   0.5492
   3.500   0.6245   0.01124   0.00392  -0.0849   0.0250   0.5524
   3.750   0.6522   0.01146   0.00414  -0.0848   0.0243   0.5555
   4.000   0.6795   0.01174   0.00442  -0.0845   0.0235   0.5587
   4.250   0.7073   0.01192   0.00464  -0.0844   0.0229   0.5622
   4.500   0.7350   0.01213   0.00487  -0.0842   0.0223   0.5656
   4.750   0.7624   0.01235   0.00512  -0.0840   0.0217   0.5690
   5.000   0.7898   0.01259   0.00536  -0.0838   0.0212   0.5722
   5.250   0.8170   0.01284   0.00562  -0.0835   0.0206   0.5754
   5.500   0.8439   0.01314   0.00594  -0.0832   0.0200   0.5792
   5.750   0.8707   0.01345   0.00629  -0.0829   0.0196   0.5830
   6.000   0.8976   0.01373   0.00661  -0.0826   0.0193   0.5865
   6.250   0.9243   0.01403   0.00694  -0.0822   0.0189   0.5899
   6.500   0.9510   0.01432   0.00727  -0.0819   0.0184   0.5933
   6.750   0.9777   0.01460   0.00759  -0.0816   0.0179   0.5975
   7.000   1.0043   0.01488   0.00789  -0.0812   0.0175   0.6016
   7.250   1.0306   0.01519   0.00822  -0.0808   0.0171   0.6055
   7.500   1.0562   0.01562   0.00868  -0.0803   0.0167   0.6089
   7.750   1.0819   0.01602   0.00914  -0.0798   0.0164   0.6131
   8.000   1.1077   0.01641   0.00960  -0.0793   0.0162   0.6177
   8.250   1.1331   0.01683   0.01008  -0.0788   0.0159   0.6222
   8.500   1.1584   0.01726   0.01057  -0.0783   0.0156   0.6260
   8.750   1.1835   0.01769   0.01107  -0.0777   0.0154   0.6303
   9.000   1.2084   0.01813   0.01157  -0.0771   0.0151   0.6353
   9.250   1.2332   0.01857   0.01208  -0.0765   0.0148   0.6404
   9.500   1.2577   0.01904   0.01260  -0.0758   0.0146   0.6450
   9.750   1.2819   0.01951   0.01314  -0.0751   0.0144   0.6501
  10.000   1.3058   0.02002   0.01371  -0.0744   0.0142   0.6555
  10.250   1.3290   0.02062   0.01437  -0.0736   0.0140   0.6610
  10.500   1.3510   0.02135   0.01520  -0.0726   0.0137   0.6672
  10.750   1.3729   0.02208   0.01603  -0.0716   0.0136   0.6738
  11.000   1.3948   0.02276   0.01681  -0.0706   0.0135   0.6798
  11.250   1.4160   0.02349   0.01766  -0.0695   0.0134   0.6864
  11.500   1.4366   0.02427   0.01856  -0.0683   0.0133   0.6935
  11.750   1.4566   0.02507   0.01948  -0.0671   0.0131   0.7005
  12.000   1.4761   0.02589   0.02042  -0.0658   0.0130   0.7082
  12.250   1.4949   0.02674   0.02138  -0.0644   0.0128   0.7149
  12.500   1.5131   0.02759   0.02236  -0.0630   0.0127   0.7221
  12.750   1.5302   0.02851   0.02339  -0.0614   0.0125   0.7290
  13.000   1.5462   0.02946   0.02447  -0.0597   0.0124   0.7362
  13.250   1.5609   0.03049   0.02563  -0.0578   0.0123   0.7444
  13.500   1.5742   0.03156   0.02682  -0.0558   0.0122   0.7530
  14.000   1.5943   0.03386   0.02941  -0.0509   0.0120   0.7728
  14.250   1.5975   0.03506   0.03074  -0.0474   0.0119   0.7843
  14.500   1.6003   0.03644   0.03227  -0.0442   0.0118   0.7986
  14.750   1.6016   0.03798   0.03398  -0.0410   0.0118   0.8169
  15.000   1.6010   0.03972   0.03590  -0.0380   0.0117   0.8432
  15.250   1.5951   0.04139   0.03790  -0.0344   0.0117   1.0000
  15.500   1.5904   0.04374   0.04038  -0.0319   0.0116   1.0000
  15.750   1.5825   0.04655   0.04334  -0.0297   0.0115   1.0000
  16.000   1.5704   0.05002   0.04696  -0.0281   0.0115   1.0000
  16.250   1.5525   0.05455   0.05167  -0.0275   0.0115   1.0000
  16.500   1.5261   0.06090   0.05823  -0.0288   0.0115   1.0000
<< Back to NPL 9510 AIRFOIL (npl9510-il)

Polar data table (+)

Polar graphs


<< Back to NPL 9510 AIRFOIL (npl9510-il)