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NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il)
Reynolds number: 100,000
Max Cl/Cd: 28.8 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nplx-il-100000-n5.txt
Download as CSV file: xf-nplx-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL AIRFOIL FROM ARC CP 1372                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5976   0.08964   0.08392  -0.0349   1.0000   0.0283
 -10.000  -0.6197   0.08022   0.07449  -0.0409   1.0000   0.0275
  -9.750  -0.6582   0.07039   0.06453  -0.0467   1.0000   0.0264
  -9.500  -0.6825   0.06518   0.05921  -0.0485   1.0000   0.0264
  -9.250  -0.7242   0.05918   0.05296  -0.0479   1.0000   0.0257
  -9.000  -0.7301   0.05727   0.05100  -0.0462   1.0000   0.0262
  -8.750  -0.7442   0.05350   0.04699  -0.0444   1.0000   0.0261
  -8.500  -0.7475   0.05074   0.04405  -0.0426   1.0000   0.0265
  -8.250  -0.7499   0.04756   0.04060  -0.0407   1.0000   0.0267
  -8.000  -0.7486   0.04444   0.03718  -0.0388   1.0000   0.0270
  -7.750  -0.7441   0.04136   0.03376  -0.0368   1.0000   0.0272
  -7.500  -0.7361   0.03849   0.03055  -0.0350   1.0000   0.0276
  -7.250  -0.7251   0.03585   0.02755  -0.0332   1.0000   0.0281
  -7.000  -0.7115   0.03335   0.02469  -0.0315   1.0000   0.0289
  -6.750  -0.6957   0.03102   0.02197  -0.0299   1.0000   0.0298
  -6.500  -0.6783   0.02907   0.01976  -0.0284   1.0000   0.0310
  -6.250  -0.6606   0.02784   0.01850  -0.0271   1.0000   0.0322
  -6.000  -0.6422   0.02667   0.01724  -0.0258   1.0000   0.0339
  -5.750  -0.6230   0.02551   0.01582  -0.0243   1.0000   0.0373
  -5.500  -0.6051   0.02467   0.01508  -0.0232   1.0000   0.0402
  -5.250  -0.5858   0.02392   0.01417  -0.0218   1.0000   0.0448
  -5.000  -0.5675   0.02299   0.01332  -0.0206   1.0000   0.0485
  -4.750  -0.5482   0.02227   0.01254  -0.0192   1.0000   0.0535
  -4.500  -0.5297   0.02138   0.01165  -0.0178   1.0000   0.0572
  -4.250  -0.5106   0.02077   0.01106  -0.0166   1.0000   0.0626
  -4.000  -0.4917   0.02007   0.01034  -0.0153   1.0000   0.0675
  -3.750  -0.4723   0.01950   0.00981  -0.0141   1.0000   0.0739
  -3.500  -0.4525   0.01893   0.00921  -0.0131   1.0000   0.0811
  -3.250  -0.4320   0.01842   0.00868  -0.0121   1.0000   0.0905
  -3.000  -0.4095   0.01784   0.00813  -0.0118   0.9995   0.1042
  -2.750  -0.3770   0.01718   0.00762  -0.0135   0.9956   0.1323
  -2.500  -0.3468   0.01581   0.00685  -0.0154   0.9922   0.2473
  -2.250  -0.3211   0.01505   0.00731  -0.0156   0.9879   0.5428
  -2.000  -0.2883   0.01531   0.00755  -0.0165   0.9839   0.5870
  -1.750  -0.2595   0.01553   0.00778  -0.0164   0.9785   0.6150
  -1.500  -0.2287   0.01581   0.00806  -0.0167   0.9740   0.6394
  -1.250  -0.1998   0.01604   0.00830  -0.0166   0.9691   0.6589
  -1.000  -0.1704   0.01620   0.00845  -0.0168   0.9638   0.6740
  -0.750  -0.1363   0.01628   0.00848  -0.0181   0.9598   0.6852
  -0.500  -0.1073   0.01627   0.00846  -0.0183   0.9534   0.6907
  -0.250  -0.0735   0.01624   0.00838  -0.0197   0.9483   0.6958
   0.000  -0.0376   0.01622   0.00830  -0.0216   0.9442   0.7007
   0.250  -0.0103   0.01620   0.00830  -0.0217   0.9375   0.7044
   0.500   0.0243   0.01617   0.00829  -0.0231   0.9326   0.7086
   0.750   0.0583   0.01610   0.00823  -0.0244   0.9252   0.7137
   1.000   0.1004   0.01591   0.00807  -0.0270   0.9165   0.7185
   1.250   0.1375   0.01569   0.00792  -0.0284   0.9046   0.7233
   1.500   0.1774   0.01550   0.00778  -0.0304   0.8960   0.7292
   1.750   0.2118   0.01538   0.00775  -0.0315   0.8873   0.7344
   2.000   0.2478   0.01512   0.00760  -0.0324   0.8735   0.7395
   2.250   0.2914   0.01465   0.00719  -0.0343   0.8524   0.7458
   2.500   0.3252   0.01430   0.00692  -0.0344   0.8236   0.7515
   2.750   0.3589   0.01400   0.00664  -0.0343   0.7813   0.7581
   3.000   0.3893   0.01383   0.00629  -0.0334   0.6976   0.7650
   3.250   0.4133   0.01445   0.00591  -0.0313   0.4775   0.7713
   3.500   0.4280   0.01563   0.00622  -0.0290   0.3132   0.7794
   3.750   0.4441   0.01681   0.00662  -0.0272   0.1603   0.7867
   4.000   0.4651   0.01762   0.00710  -0.0261   0.1145   0.7960
   4.250   0.4868   0.01821   0.00762  -0.0249   0.0982   0.8052
   4.500   0.5091   0.01871   0.00819  -0.0237   0.0887   0.8155
   4.750   0.5304   0.01935   0.00881  -0.0225   0.0819   0.8271
   5.000   0.5521   0.01981   0.00938  -0.0212   0.0759   0.8391
   5.250   0.5730   0.02037   0.00996  -0.0199   0.0712   0.8529
   5.500   0.5937   0.02106   0.01071  -0.0185   0.0682   0.8698
   5.750   0.6162   0.02169   0.01146  -0.0173   0.0657   0.8899
   6.000   0.6416   0.02243   0.01230  -0.0168   0.0634   0.9176
   6.500   0.7033   0.02442   0.01424  -0.0188   0.0581   1.0000
   6.750   0.7303   0.02549   0.01540  -0.0188   0.0561   1.0000
   7.000   0.7572   0.02670   0.01675  -0.0188   0.0546   1.0000
   7.250   0.7835   0.02806   0.01824  -0.0187   0.0533   1.0000
   7.500   0.8088   0.02951   0.01984  -0.0185   0.0522   1.0000
   7.750   0.8329   0.03099   0.02147  -0.0181   0.0510   1.0000
   8.000   0.8557   0.03236   0.02297  -0.0177   0.0497   1.0000
   8.250   0.8776   0.03380   0.02445  -0.0172   0.0483   1.0000
   8.500   0.8972   0.03576   0.02665  -0.0164   0.0472   1.0000
   8.750   0.9143   0.03800   0.02929  -0.0151   0.0464   1.0000
   9.000   0.9287   0.04054   0.03225  -0.0136   0.0458   1.0000
   9.250   0.9399   0.04334   0.03546  -0.0118   0.0453   1.0000
   9.500   0.9475   0.04642   0.03894  -0.0099   0.0449   1.0000
   9.750   0.9513   0.04966   0.04257  -0.0079   0.0444   1.0000
  10.000   0.9513   0.05298   0.04624  -0.0057   0.0437   1.0000
  10.250   0.9481   0.05624   0.04980  -0.0036   0.0430   1.0000
  10.500   0.9409   0.05956   0.05338  -0.0015   0.0425   1.0000
  10.750   0.9269   0.06286   0.05688   0.0011   0.0421   1.0000
  11.000   0.9056   0.06679   0.06101   0.0030   0.0420   1.0000
  11.250   0.8755   0.07219   0.06662   0.0029   0.0422   1.0000
  11.500   0.8365   0.08026   0.07488  -0.0010   0.0426   1.0000
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