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NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NLR-7301 AIRFOIL (nlr7301-il)
Reynolds number: 100,000
Max Cl/Cd: 21.5 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlr7301-il-100000.txt
Download as CSV file: xf-nlr7301-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7301 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7978   0.06937   0.06245  -0.0695   1.0000   0.1013
 -11.750  -0.8143   0.06582   0.05882  -0.0683   1.0000   0.1010
 -11.500  -0.8382   0.06327   0.05621  -0.0651   1.0000   0.1007
 -11.250  -0.8672   0.06151   0.05441  -0.0600   1.0000   0.1004
 -11.000  -0.8932   0.05949   0.05229  -0.0553   1.0000   0.1002
 -10.750  -0.9158   0.05731   0.04995  -0.0509   1.0000   0.0999
 -10.500  -0.9339   0.05494   0.04738  -0.0469   1.0000   0.0998
 -10.250  -0.9468   0.05245   0.04462  -0.0435   1.0000   0.0998
 -10.000  -0.9538   0.04997   0.04186  -0.0405   1.0000   0.1001
  -9.750  -0.9579   0.04758   0.03911  -0.0378   1.0000   0.1008
  -9.500  -0.9553   0.04528   0.03650  -0.0357   1.0000   0.1018
  -9.250  -0.9385   0.04380   0.03516  -0.0345   1.0000   0.1035
  -9.000  -0.9257   0.04234   0.03364  -0.0331   1.0000   0.1052
  -8.750  -0.9136   0.04067   0.03178  -0.0316   1.0000   0.1069
  -8.500  -0.9004   0.03894   0.02978  -0.0303   1.0000   0.1086
  -8.250  -0.8860   0.03734   0.02782  -0.0291   1.0000   0.1105
  -8.000  -0.8674   0.03587   0.02638  -0.0282   1.0000   0.1130
  -7.750  -0.8482   0.03486   0.02539  -0.0272   1.0000   0.1159
  -7.500  -0.8290   0.03376   0.02413  -0.0263   1.0000   0.1191
  -7.250  -0.8091   0.03257   0.02275  -0.0255   1.0000   0.1222
  -7.000  -0.7887   0.03157   0.02190  -0.0246   1.0000   0.1258
  -6.750  -0.7681   0.03075   0.02102  -0.0237   1.0000   0.1304
  -6.500  -0.7473   0.02978   0.02005  -0.0228   1.0000   0.1350
  -6.250  -0.7266   0.02901   0.01939  -0.0219   1.0000   0.1402
  -6.000  -0.7052   0.02826   0.01857  -0.0212   1.0000   0.1466
  -5.750  -0.6847   0.02749   0.01801  -0.0202   1.0000   0.1535
  -5.500  -0.6633   0.02678   0.01734  -0.0195   1.0000   0.1619
  -5.250  -0.6417   0.02614   0.01682  -0.0189   1.0000   0.1722
  -5.000  -0.6202   0.02541   0.01631  -0.0183   1.0000   0.1844
  -4.750  -0.5976   0.02472   0.01583  -0.0180   1.0000   0.2010
  -4.500  -0.5736   0.02397   0.01533  -0.0181   1.0000   0.2264
  -4.250  -0.5448   0.02257   0.01462  -0.0200   1.0000   0.2879
  -4.000  -0.5219   0.02203   0.01583  -0.0192   1.0000   0.5276
  -3.750  -0.5027   0.02315   0.01693  -0.0168   1.0000   0.5842
  -3.500  -0.4886   0.02443   0.01822  -0.0129   1.0000   0.6077
  -3.250  -0.4729   0.02557   0.01933  -0.0096   1.0000   0.6267
  -3.000  -0.4591   0.02673   0.02049  -0.0058   1.0000   0.6414
  -2.750  -0.4473   0.02784   0.02162  -0.0014   1.0000   0.6524
  -2.500  -0.4251   0.02869   0.02241  -0.0001   0.9990   0.6685
  -2.250  -0.4038   0.03026   0.02402   0.0035   0.9941   0.6774
  -2.000  -0.3719   0.03119   0.02488   0.0030   0.9886   0.6924
  -1.750  -0.3497   0.03239   0.02611   0.0059   0.9827   0.7018
  -1.500  -0.3178   0.03314   0.02681   0.0052   0.9767   0.7156
  -1.250  -0.2970   0.03400   0.02769   0.0080   0.9698   0.7265
  -1.000  -0.2736   0.03501   0.02871   0.0105   0.9630   0.7425
  -0.750  -0.2546   0.03566   0.02939   0.0135   0.9549   0.7605
  -0.500  -0.2247   0.03642   0.03013   0.0138   0.9473   0.7779
  -0.250  -0.2062   0.03643   0.03017   0.0164   0.9381   0.7859
   0.000  -0.1633   0.03672   0.03042   0.0126   0.9296   0.7942
   0.250  -0.1377   0.03651   0.03021   0.0126   0.9188   0.7997
   0.500  -0.1010   0.03661   0.03032   0.0109   0.9087   0.8048
   0.750  -0.0624   0.03652   0.03023   0.0083   0.8962   0.8102
   1.000   0.0273   0.03587   0.02954  -0.0006   0.8702   0.8142
   1.250   0.0735   0.03440   0.02808  -0.0014   0.8426   0.8175
   1.500   0.1335   0.03318   0.02690  -0.0046   0.8278   0.8206
   1.750   0.1632   0.03239   0.02615  -0.0044   0.8115   0.8239
   2.000   0.2278   0.03090   0.02473  -0.0086   0.7992   0.8273
   2.250   0.2865   0.02905   0.02294  -0.0116   0.7838   0.8304
   2.500   0.3284   0.02733   0.02128  -0.0123   0.7629   0.8328
   2.750   0.3578   0.02557   0.01959  -0.0100   0.7337   0.8355
   3.000   0.3752   0.02411   0.01815  -0.0060   0.6781   0.8390
   3.250   0.3920   0.02425   0.01617  -0.0010   0.3261   0.8417
   3.500   0.3988   0.02532   0.01649   0.0015   0.2469   0.8446
   3.750   0.4189   0.02595   0.01680   0.0019   0.2144   0.8474
   4.000   0.4421   0.02653   0.01712   0.0019   0.1945   0.8507
   4.250   0.4635   0.02689   0.01735   0.0029   0.1801   0.8540
   4.500   0.4896   0.02744   0.01776   0.0030   0.1682   0.8571
   4.750   0.5195   0.02817   0.01829   0.0021   0.1583   0.8600
   5.000   0.5506   0.02880   0.01885   0.0011   0.1501   0.8630
   5.250   0.5858   0.02978   0.01970  -0.0008   0.1433   0.8660
   5.500   0.6118   0.03028   0.02021  -0.0006   0.1375   0.8693
   5.750   0.6426   0.03127   0.02102  -0.0013   0.1328   0.8731
   6.000   0.6709   0.03203   0.02194  -0.0015   0.1290   0.8770
   6.250   0.7027   0.03304   0.02297  -0.0027   0.1258   0.8804
   6.500   0.7334   0.03411   0.02401  -0.0037   0.1233   0.8836
   6.750   0.7610   0.03550   0.02540  -0.0039   0.1213   0.8870
   7.000   0.7836   0.03657   0.02677  -0.0033   0.1196   0.8911
   7.250   0.8075   0.03787   0.02831  -0.0032   0.1176   0.8958
   7.500   0.8288   0.03911   0.02974  -0.0026   0.1159   0.9003
   7.750   0.8490   0.04045   0.03124  -0.0018   0.1146   0.9051
   8.000   0.8706   0.04218   0.03316  -0.0015   0.1139   0.9097
   8.250   0.8900   0.04413   0.03535  -0.0011   0.1136   0.9141
   8.500   0.9028   0.04627   0.03782   0.0004   0.1137   0.9190
   8.750   0.9109   0.04914   0.04111   0.0019   0.1145   0.9242
   9.000   0.9127   0.05248   0.04491   0.0040   0.1159   0.9296
   9.250   0.9097   0.05589   0.04870   0.0063   0.1175   0.9361
   9.500   0.9079   0.05934   0.05244   0.0079   0.1188   0.9428
   9.750   0.9067   0.06266   0.05598   0.0095   0.1199   0.9504
  10.000   0.9124   0.06614   0.05958   0.0100   0.1209   0.9582
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