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US1000ROOT (us1000root-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: US1000ROOT (us1000root-il)
Reynolds number: 50,000
Max Cl/Cd: 24.69 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-us1000root-il-50000-n5.txt
Download as CSV file: xf-us1000root-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: US1000ROOT                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6170   0.08981   0.08113  -0.0230   1.0000   0.2551
 -11.250  -0.6549   0.07789   0.06919  -0.0264   1.0000   0.2687
 -10.750  -0.6958   0.06647   0.05776  -0.0289   1.0000   0.2839
 -10.500  -0.6709   0.06662   0.05780  -0.0276   1.0000   0.2872
 -10.250  -0.7841   0.05332   0.04462  -0.0284   1.0000   0.2992
 -10.000  -0.7771   0.05191   0.04314  -0.0270   1.0000   0.3039
  -9.750  -0.8587   0.04630   0.03751  -0.0190   1.0000   0.3098
  -9.500  -0.8487   0.04535   0.03649  -0.0169   1.0000   0.3143
  -9.250  -0.8407   0.04432   0.03538  -0.0147   1.0000   0.3190
  -9.000  -0.8686   0.04178   0.03269  -0.0089   1.0000   0.3245
  -8.750  -0.8543   0.04107   0.03193  -0.0071   1.0000   0.3291
  -8.500  -0.8456   0.04023   0.03103  -0.0046   1.0000   0.3342
  -8.250  -0.8630   0.03839   0.02900   0.0007   1.0000   0.3400
  -8.000  -0.8439   0.03800   0.02863   0.0021   1.0000   0.3443
  -7.750  -0.8384   0.03724   0.02780   0.0051   1.0000   0.3495
  -7.500  -0.8514   0.03588   0.02624   0.0104   1.0000   0.3551
  -7.250  -0.8350   0.03562   0.02597   0.0122   1.0000   0.3594
  -7.000  -0.8315   0.03496   0.02524   0.0156   1.0000   0.3644
  -6.750  -0.8375   0.03396   0.02403   0.0200   1.0000   0.3700
  -6.500  -0.8237   0.03369   0.02378   0.0221   1.0000   0.3744
  -6.250  -0.8183   0.03312   0.02312   0.0251   1.0000   0.3798
  -6.000  -0.7937   0.03242   0.02225   0.0243   0.9931   0.3865
  -5.750  -0.7541   0.03196   0.02171   0.0214   0.9816   0.3939
  -5.500  -0.7190   0.03128   0.02085   0.0190   0.9687   0.4016
  -5.250  -0.6795   0.03080   0.02028   0.0161   0.9570   0.4093
  -5.000  -0.6423   0.03022   0.01959   0.0137   0.9448   0.4172
  -4.750  -0.6048   0.02972   0.01899   0.0113   0.9326   0.4256
  -4.500  -0.5646   0.02927   0.01847   0.0087   0.9211   0.4339
  -4.250  -0.5255   0.02869   0.01775   0.0060   0.9100   0.4439
  -4.000  -0.4778   0.02830   0.01737   0.0023   0.9003   0.4530
  -3.750  -0.4376   0.02789   0.01690  -0.0003   0.8878   0.4628
  -3.500  -0.4012   0.02746   0.01640  -0.0021   0.8746   0.4737
  -3.250  -0.3623   0.02717   0.01612  -0.0041   0.8611   0.4834
  -3.000  -0.3270   0.02687   0.01580  -0.0054   0.8467   0.4940
  -2.750  -0.2954   0.02658   0.01548  -0.0060   0.8315   0.5053
  -2.500  -0.2663   0.02630   0.01515  -0.0062   0.8157   0.5173
  -2.250  -0.2350   0.02612   0.01500  -0.0065   0.7998   0.5282
  -2.000  -0.2061   0.02591   0.01480  -0.0063   0.7837   0.5402
  -1.750  -0.1791   0.02571   0.01459  -0.0058   0.7673   0.5525
  -1.500  -0.1558   0.02555   0.01444  -0.0047   0.7498   0.5652
  -1.250  -0.1313   0.02539   0.01429  -0.0038   0.7328   0.5787
  -1.000  -0.1058   0.02525   0.01415  -0.0029   0.7161   0.5927
  -0.750  -0.0800   0.02512   0.01403  -0.0021   0.6997   0.6070
  -0.500  -0.0537   0.02504   0.01394  -0.0014   0.6837   0.6218
  -0.250  -0.0273   0.02498   0.01389  -0.0006   0.6678   0.6370
   0.000  -0.0007   0.02496   0.01388   0.0001   0.6523   0.6523
   0.250   0.0259   0.02498   0.01389   0.0009   0.6369   0.6678
   0.500   0.0523   0.02504   0.01395   0.0017   0.6219   0.6837
   0.750   0.0785   0.02512   0.01403   0.0024   0.6071   0.6997
   1.000   0.1044   0.02525   0.01416   0.0032   0.5927   0.7162
   1.250   0.1298   0.02539   0.01429   0.0040   0.5787   0.7328
   1.500   0.1544   0.02554   0.01443   0.0050   0.5651   0.7498
   1.750   0.1776   0.02570   0.01460   0.0061   0.5525   0.7675
   2.000   0.2049   0.02591   0.01481   0.0066   0.5402   0.7838
   2.250   0.2338   0.02611   0.01500   0.0067   0.5284   0.7999
   2.500   0.2650   0.02630   0.01516   0.0064   0.5172   0.8158
   2.750   0.2942   0.02657   0.01548   0.0063   0.5053   0.8316
   3.000   0.3260   0.02687   0.01581   0.0056   0.4941   0.8468
   3.250   0.3615   0.02716   0.01613   0.0043   0.4835   0.8612
   3.500   0.4004   0.02746   0.01641   0.0023   0.4737   0.8747
   3.750   0.4371   0.02788   0.01692   0.0004   0.4628   0.8879
   4.000   0.4772   0.02829   0.01739  -0.0021   0.4530   0.9003
   4.250   0.5247   0.02867   0.01776  -0.0058   0.4438   0.9102
   4.500   0.5640   0.02926   0.01849  -0.0085   0.4339   0.9212
   4.750   0.6041   0.02970   0.01901  -0.0112   0.4256   0.9327
   5.000   0.6418   0.03021   0.01962  -0.0136   0.4171   0.9449
   5.250   0.6788   0.03078   0.02030  -0.0160   0.4092   0.9572
   5.500   0.7183   0.03127   0.02088  -0.0188   0.4015   0.9689
   5.750   0.7535   0.03194   0.02175  -0.0212   0.3936   0.9818
   6.000   0.7930   0.03241   0.02230  -0.0242   0.3865   0.9932
   6.250   0.8174   0.03310   0.02316  -0.0248   0.3797   1.0000
   6.500   0.8229   0.03368   0.02384  -0.0218   0.3744   1.0000
   6.750   0.8366   0.03396   0.02410  -0.0198   0.3700   1.0000
   7.000   0.8310   0.03494   0.02528  -0.0154   0.3644   1.0000
   7.250   0.8345   0.03560   0.02602  -0.0120   0.3593   1.0000
   7.500   0.8503   0.03590   0.02634  -0.0101   0.3552   1.0000
   7.750   0.8383   0.03721   0.02785  -0.0050   0.3494   1.0000
   8.000   0.8439   0.03799   0.02869  -0.0020   0.3443   1.0000
   8.250   0.8636   0.03836   0.02905  -0.0006   0.3400   1.0000
   8.500   0.8460   0.04023   0.03112   0.0047   0.3343   1.0000
   8.750   0.8543   0.04109   0.03205   0.0072   0.3291   1.0000
   9.000   0.8706   0.04172   0.03273   0.0089   0.3246   1.0000
   9.250   0.8415   0.04432   0.03550   0.0147   0.3191   1.0000
   9.500   0.8486   0.04541   0.03666   0.0171   0.3143   1.0000
   9.750   0.8654   0.04612   0.03744   0.0185   0.3101   1.0000
  10.000   0.7788   0.05190   0.04325   0.0270   0.3040   1.0000
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