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NLR-1T AIRFOIL (nlr1t-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NLR-1T AIRFOIL (nlr1t-il)
Reynolds number: 100,000
Max Cl/Cd: 38.93 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlr1t-il-100000.txt
Download as CSV file: xf-nlr1t-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-1T 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4155   0.10528   0.10056  -0.0216   1.0000   0.0939
  -9.750  -0.4342   0.10193   0.09728  -0.0258   1.0000   0.0953
  -9.500  -0.4538   0.09814   0.09356  -0.0303   1.0000   0.0957
  -9.250  -0.4160   0.09327   0.08866  -0.0236   1.0000   0.1007
  -9.000  -0.4162   0.08962   0.08503  -0.0242   1.0000   0.1046
  -8.750  -0.4295   0.08556   0.08104  -0.0271   1.0000   0.1082
  -8.500  -0.4549   0.08114   0.07670  -0.0322   1.0000   0.1094
  -8.250  -0.4826   0.07750   0.07310  -0.0339   1.0000   0.1097
  -8.000  -0.4433   0.07318   0.06881  -0.0289   1.0000   0.1163
  -7.750  -0.4592   0.06950   0.06520  -0.0295   1.0000   0.1186
  -7.500  -0.4824   0.06673   0.06248  -0.0275   1.0000   0.1201
  -7.250  -0.5083   0.06394   0.05969  -0.0255   1.0000   0.1222
  -7.000  -0.5449   0.06199   0.05754  -0.0230   1.0000   0.1241
  -6.750  -0.5350   0.05706   0.05277  -0.0209   1.0000   0.1277
  -6.500  -0.5340   0.05426   0.04997  -0.0183   1.0000   0.1331
  -6.250  -0.5961   0.06364   0.05827  -0.0168   1.0000   0.1393
  -6.000  -0.5802   0.05821   0.05322  -0.0151   1.0000   0.1433
  -5.750  -0.5802   0.05575   0.05056  -0.0130   1.0000   0.1557
  -5.500  -0.5757   0.05341   0.04808  -0.0107   1.0000   0.1697
  -5.250  -0.5679   0.05074   0.04538  -0.0085   1.0000   0.1847
  -5.000  -0.5583   0.04810   0.04277  -0.0062   1.0000   0.2009
  -3.750  -0.4474   0.03048   0.02189   0.0026   1.0000   0.0803
  -3.500  -0.4230   0.02757   0.01870   0.0037   1.0000   0.0737
  -3.250  -0.3970   0.02673   0.01720   0.0058   1.0000   0.0679
  -3.000  -0.3705   0.02457   0.01485   0.0064   1.0000   0.0667
  -2.750  -0.3437   0.02307   0.01318   0.0071   1.0000   0.0665
  -2.500  -0.3172   0.02173   0.01173   0.0077   1.0000   0.0692
  -2.250  -0.2916   0.02051   0.01058   0.0083   1.0000   0.0729
  -2.000  -0.2668   0.01958   0.00965   0.0092   1.0000   0.0761
  -1.750  -0.1184   0.01477   0.00838  -0.0121   1.0000   1.0000
  -1.500  -0.1039   0.01478   0.00806  -0.0097   1.0000   1.0000
  -1.250  -0.0888   0.01481   0.00786  -0.0076   1.0000   1.0000
  -1.000  -0.0729   0.01486   0.00773  -0.0055   1.0000   1.0000
  -0.750  -0.0565   0.01493   0.00764  -0.0036   1.0000   1.0000
  -0.500  -0.0397   0.01502   0.00759  -0.0018   1.0000   1.0000
  -0.250  -0.0225   0.01514   0.00758  -0.0001   1.0000   1.0000
   0.000  -0.0051   0.01527   0.00762   0.0016   1.0000   1.0000
   0.250   0.0127   0.01543   0.00769   0.0031   1.0000   1.0000
   0.500   0.0307   0.01561   0.00779   0.0046   1.0000   1.0000
   0.750   0.0489   0.01582   0.00795   0.0059   1.0000   1.0000
   1.000   0.0673   0.01606   0.00815   0.0072   1.0000   1.0000
   1.250   0.0857   0.01633   0.00840   0.0084   1.0000   1.0000
   1.500   0.1641   0.01689   0.00896  -0.0024   0.9835   1.0000
   1.750   0.2290   0.01716   0.00929  -0.0103   0.9685   1.0000
   2.000   0.2929   0.01718   0.00941  -0.0175   0.9507   1.0000
   2.250   0.3647   0.01693   0.00930  -0.0258   0.9319   1.0000
   2.500   0.4490   0.01618   0.00879  -0.0359   0.9123   1.0000
   2.750   0.4991   0.01534   0.00812  -0.0384   0.8830   1.0000
   3.000   0.5273   0.01452   0.00743  -0.0362   0.8406   1.0000
   3.250   0.5380   0.01394   0.00691  -0.0308   0.7440   1.0000
   3.500   0.5649   0.01451   0.00569  -0.0272   0.4518   1.0000
   3.750   0.5837   0.01563   0.00617  -0.0255   0.3778   1.0000
   4.000   0.6057   0.01643   0.00671  -0.0244   0.3442   1.0000
   4.250   0.6289   0.01713   0.00725  -0.0235   0.3223   1.0000
   4.500   0.6527   0.01782   0.00782  -0.0228   0.3061   1.0000
   4.750   0.6768   0.01849   0.00844  -0.0221   0.2923   1.0000
   5.000   0.7005   0.01914   0.00911  -0.0213   0.2787   1.0000
   5.250   0.7231   0.01974   0.00966  -0.0205   0.2631   1.0000
   5.500   0.7452   0.02032   0.01020  -0.0195   0.2472   1.0000
   5.750   0.7675   0.02093   0.01083  -0.0186   0.2330   1.0000
   6.000   0.7897   0.02160   0.01158  -0.0177   0.2191   1.0000
   6.250   0.8112   0.02230   0.01228  -0.0167   0.2035   1.0000
   6.500   0.8316   0.02306   0.01305  -0.0155   0.1854   1.0000
   6.750   0.8508   0.02389   0.01401  -0.0140   0.1646   1.0000
   7.000   0.8711   0.02499   0.01506  -0.0127   0.1467   1.0000
   7.250   0.8915   0.02615   0.01631  -0.0114   0.1327   1.0000
   7.500   0.9117   0.02732   0.01765  -0.0100   0.1218   1.0000
   7.750   0.9329   0.02862   0.01895  -0.0090   0.1145   1.0000
   8.000   0.9530   0.03015   0.02082  -0.0075   0.1085   1.0000
   8.250   0.9742   0.03156   0.02228  -0.0065   0.1042   1.0000
   8.500   0.9916   0.03386   0.02498  -0.0049   0.1010   1.0000
   8.750   1.0063   0.03599   0.02756  -0.0028   0.0972   1.0000
   9.000   1.0236   0.03742   0.02912  -0.0014   0.0934   1.0000
   9.250   1.0405   0.03970   0.03149  -0.0001   0.0910   1.0000
   9.500   1.0464   0.04316   0.03547   0.0026   0.0898   1.0000
   9.750   1.0461   0.04703   0.03992   0.0059   0.0890   1.0000
  10.000   1.0394   0.05127   0.04469   0.0095   0.0881   1.0000
  10.250   1.0268   0.05576   0.04963   0.0130   0.0872   1.0000
  10.500   1.0088   0.06049   0.05472   0.0163   0.0869   1.0000
  10.750   0.9855   0.06538   0.05987   0.0192   0.0872   1.0000
  11.000   0.9577   0.07001   0.06466   0.0220   0.0879   1.0000
  11.250   0.9309   0.07525   0.07000   0.0228   0.0888   1.0000
  11.500   0.9077   0.08113   0.07595   0.0219   0.0896   1.0000
  11.750   0.8906   0.08743   0.08229   0.0200   0.0902   1.0000
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