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NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NPL 9510 AIRFOIL (npl9510-il)
Reynolds number: 200,000
Max Cl/Cd: 32.42 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-npl9510-il-200000-n5.txt
Download as CSV file: xf-npl9510-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.9330   0.12446   0.11985  -0.0152   1.0000   0.0252
 -16.750  -0.9729   0.11115   0.10630  -0.0232   1.0000   0.0250
 -16.500  -1.0002   0.10138   0.09630  -0.0290   1.0000   0.0250
 -16.250  -1.0215   0.09330   0.08800  -0.0338   1.0000   0.0251
 -16.000  -1.0387   0.08638   0.08088  -0.0378   1.0000   0.0252
 -15.750  -1.0527   0.08034   0.07462  -0.0411   1.0000   0.0253
 -15.500  -1.0642   0.07496   0.06903  -0.0439   1.0000   0.0255
 -15.250  -1.0725   0.07034   0.06422  -0.0461   1.0000   0.0256
 -15.000  -1.0738   0.06699   0.06078  -0.0472   1.0000   0.0258
 -14.750  -1.0743   0.06388   0.05759  -0.0482   1.0000   0.0261
 -14.500  -1.0742   0.06089   0.05452  -0.0491   1.0000   0.0263
 -14.250  -1.0733   0.05804   0.05158  -0.0499   1.0000   0.0266
 -14.000  -1.0719   0.05531   0.04875  -0.0506   1.0000   0.0269
 -13.750  -1.0696   0.05271   0.04605  -0.0511   1.0000   0.0272
 -13.500  -1.0664   0.05027   0.04351  -0.0516   1.0000   0.0276
 -13.250  -1.0623   0.04794   0.04107  -0.0519   1.0000   0.0280
 -13.000  -1.0576   0.04574   0.03876  -0.0521   1.0000   0.0285
 -12.750  -1.0520   0.04366   0.03656  -0.0522   1.0000   0.0290
 -12.500  -1.0457   0.04171   0.03446  -0.0521   1.0000   0.0296
 -12.250  -1.0387   0.03988   0.03250  -0.0520   1.0000   0.0302
 -12.000  -1.0325   0.03810   0.03073  -0.0515   1.0000   0.0307
 -11.750  -1.0262   0.03643   0.02903  -0.0510   1.0000   0.0313
 -11.500  -1.0205   0.03484   0.02740  -0.0503   1.0000   0.0319
 -11.250  -1.0166   0.03336   0.02587  -0.0491   1.0000   0.0324
 -11.000  -1.0145   0.03195   0.02440  -0.0475   1.0000   0.0330
 -10.750  -1.0076   0.03053   0.02292  -0.0466   1.0000   0.0338
 -10.500  -0.9980   0.02915   0.02146  -0.0461   1.0000   0.0346
 -10.250  -0.9863   0.02781   0.02004  -0.0458   1.0000   0.0355
 -10.000  -0.9735   0.02640   0.01861  -0.0459   1.0000   0.0366
  -9.750  -0.9578   0.02529   0.01745  -0.0457   1.0000   0.0381
  -9.500  -0.9404   0.02430   0.01638  -0.0455   1.0000   0.0399
  -9.250  -0.9217   0.02332   0.01533  -0.0453   1.0000   0.0417
  -9.000  -0.9021   0.02228   0.01428  -0.0455   1.0000   0.0439
  -8.750  -0.8809   0.02143   0.01336  -0.0455   1.0000   0.0466
  -8.500  -0.8587   0.02057   0.01247  -0.0458   1.0000   0.0498
  -8.250  -0.8356   0.01980   0.01169  -0.0460   1.0000   0.0545
  -8.000  -0.8117   0.01903   0.01092  -0.0464   1.0000   0.0607
  -7.750  -0.7871   0.01832   0.01023  -0.0468   1.0000   0.0690
  -7.500  -0.7618   0.01767   0.00962  -0.0473   1.0000   0.0803
  -7.250  -0.7361   0.01708   0.00906  -0.0477   1.0000   0.0945
  -7.000  -0.7099   0.01655   0.00857  -0.0482   1.0000   0.1100
  -6.750  -0.6832   0.01602   0.00810  -0.0488   1.0000   0.1263
  -6.500  -0.6561   0.01551   0.00764  -0.0495   1.0000   0.1439
  -6.250  -0.6285   0.01503   0.00722  -0.0501   1.0000   0.1628
  -6.000  -0.6005   0.01455   0.00681  -0.0509   1.0000   0.1850
  -5.750  -0.5711   0.01396   0.00637  -0.0521   1.0000   0.2189
  -5.500  -0.5398   0.01324   0.00595  -0.0539   1.0000   0.2780
  -5.250  -0.5089   0.01270   0.00575  -0.0554   1.0000   0.3482
  -5.000  -0.4790   0.01252   0.00571  -0.0562   0.9996   0.3935
  -4.750  -0.4468   0.01245   0.00569  -0.0573   0.9983   0.4207
  -4.500  -0.4142   0.01243   0.00566  -0.0584   0.9968   0.4404
  -4.250  -0.3814   0.01243   0.00565  -0.0595   0.9953   0.4544
  -4.000  -0.3483   0.01246   0.00567  -0.0607   0.9940   0.4664
  -3.750  -0.3173   0.01246   0.00565  -0.0614   0.9922   0.4769
  -3.500  -0.2860   0.01249   0.00565  -0.0622   0.9904   0.4862
  -3.250  -0.2546   0.01253   0.00570  -0.0630   0.9887   0.4951
  -3.000  -0.2223   0.01258   0.00571  -0.0640   0.9871   0.5063
  -2.750  -0.1902   0.01269   0.00588  -0.0648   0.9855   0.5167
  -2.500  -0.1570   0.01280   0.00601  -0.0659   0.9841   0.5271
  -2.250  -0.1272   0.01287   0.00610  -0.0663   0.9818   0.5349
  -2.000  -0.0969   0.01290   0.00611  -0.0669   0.9796   0.5409
  -1.750  -0.0662   0.01293   0.00621  -0.0675   0.9775   0.5447
  -1.500  -0.0342   0.01296   0.00628  -0.0684   0.9755   0.5492
  -1.250  -0.0012   0.01299   0.00632  -0.0695   0.9739   0.5541
  -1.000   0.0319   0.01302   0.00639  -0.0707   0.9725   0.5584
  -0.750   0.0636   0.01307   0.00652  -0.0715   0.9707   0.5620
  -0.500   0.0937   0.01306   0.00659  -0.0719   0.9655   0.5660
  -0.250   0.1723   0.01199   0.00557  -0.0808   0.9420   0.5717
   0.000   0.2120   0.01139   0.00502  -0.0820   0.9130   0.5758
   0.250   0.2470   0.01105   0.00473  -0.0824   0.8786   0.5793
   0.500   0.2714   0.01186   0.00413  -0.0797   0.5282   0.5828
   0.750   0.2833   0.01398   0.00464  -0.0773   0.1566   0.5864
   1.000   0.3091   0.01454   0.00486  -0.0771   0.0898   0.5908
   1.250   0.3356   0.01490   0.00513  -0.0767   0.0709   0.5942
   1.500   0.3625   0.01521   0.00543  -0.0764   0.0622   0.5975
   1.750   0.3896   0.01552   0.00576  -0.0761   0.0574   0.6012
   2.000   0.4166   0.01586   0.00609  -0.0759   0.0536   0.6054
   2.250   0.4436   0.01626   0.00647  -0.0757   0.0505   0.6097
   2.500   0.4700   0.01662   0.00688  -0.0752   0.0477   0.6130
   2.750   0.4962   0.01706   0.00733  -0.0748   0.0457   0.6166
   3.000   0.5220   0.01765   0.00789  -0.0744   0.0442   0.6205
   3.250   0.5490   0.01812   0.00841  -0.0741   0.0423   0.6250
   3.500   0.5755   0.01860   0.00893  -0.0737   0.0404   0.6288
   3.750   0.6016   0.01915   0.00949  -0.0733   0.0390   0.6325
   4.000   0.6275   0.01994   0.01026  -0.0729   0.0379   0.6365
   4.250   0.6546   0.02061   0.01104  -0.0726   0.0368   0.6408
   4.500   0.6815   0.02128   0.01181  -0.0722   0.0352   0.6452
   4.750   0.7078   0.02190   0.01251  -0.0718   0.0339   0.6490
   5.000   0.7340   0.02264   0.01329  -0.0715   0.0330   0.6534
   5.250   0.7603   0.02368   0.01439  -0.0712   0.0323   0.6581
   5.500   0.7867   0.02486   0.01584  -0.0707   0.0314   0.6624
   5.750   0.8121   0.02605   0.01730  -0.0700   0.0303   0.6665
   6.000   0.8371   0.02704   0.01845  -0.0694   0.0293   0.6713
   6.250   0.8619   0.02788   0.01938  -0.0690   0.0285   0.6767
   6.500   0.8859   0.02886   0.02044  -0.0685   0.0279   0.6811
   6.750   0.9078   0.03092   0.02293  -0.0673   0.0273   0.6854
   7.000   0.9266   0.03386   0.02643  -0.0657   0.0266   0.6904
   7.250   0.9425   0.03725   0.03035  -0.0638   0.0260   0.6957
   7.500   0.9549   0.04087   0.03450  -0.0617   0.0254   0.6998
   7.750   0.9671   0.04398   0.03799  -0.0598   0.0248   0.7046
   8.000   0.9811   0.04614   0.04037  -0.0584   0.0243   0.7101
   8.250   0.9969   0.04751   0.04186  -0.0572   0.0240   0.7154
   8.500   1.0110   0.04894   0.04342  -0.0559   0.0237   0.7211
   8.750   0.9994   0.05574   0.05081  -0.0525   0.0233   0.7255
   9.000   0.9749   0.06450   0.06011  -0.0492   0.0232   0.7291
   9.250   0.9513   0.07176   0.06772  -0.0471   0.0232   0.7323
   9.500   0.9275   0.07713   0.07328  -0.0452   0.0233   0.7366
   9.750   0.9033   0.08345   0.07975  -0.0459   0.0233   0.7411
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