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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 500,000
Max Cl/Cd: 59.07 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du8608418-il-500000-n5.txt
Download as CSV file: xf-du8608418-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DU86-084/18 8.44%                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5449   0.08419   0.08149  -0.0224   0.8486   0.0047
  -9.250  -0.5497   0.07909   0.07642  -0.0255   0.8482   0.0047
  -9.000  -0.5592   0.07324   0.07060  -0.0298   0.8477   0.0046
  -8.750  -0.5759   0.06687   0.06424  -0.0349   0.8470   0.0045
  -8.250  -0.6029   0.05584   0.05302  -0.0370   0.8458   0.0044
  -8.000  -0.6101   0.04974   0.04673  -0.0369   0.8452   0.0043
  -7.750  -0.6139   0.04353   0.04023  -0.0358   0.8444   0.0041
  -7.500  -0.6182   0.03608   0.03233  -0.0336   0.8438   0.0039
  -7.250  -0.6213   0.02775   0.02321  -0.0301   0.8432   0.0037
  -7.000  -0.6081   0.02370   0.01861  -0.0282   0.8427   0.0036
  -6.750  -0.5889   0.02114   0.01563  -0.0269   0.8423   0.0037
  -6.500  -0.5673   0.01919   0.01335  -0.0260   0.8417   0.0038
  -6.250  -0.5441   0.01770   0.01161  -0.0253   0.8411   0.0040
  -6.000  -0.5202   0.01643   0.01011  -0.0246   0.8407   0.0042
  -5.750  -0.4957   0.01540   0.00892  -0.0241   0.8403   0.0046
  -5.500  -0.4708   0.01457   0.00794  -0.0236   0.8398   0.0051
  -5.250  -0.4453   0.01395   0.00722  -0.0232   0.8392   0.0056
  -5.000  -0.4210   0.01306   0.00621  -0.0227   0.8385   0.0064
  -4.750  -0.3950   0.01262   0.00575  -0.0225   0.8379   0.0075
  -4.500  -0.3683   0.01236   0.00546  -0.0224   0.8373   0.0092
  -4.250  -0.3421   0.01190   0.00492  -0.0221   0.8365   0.0104
  -4.000  -0.3159   0.01145   0.00438  -0.0218   0.8359   0.0126
  -3.750  -0.2891   0.01120   0.00409  -0.0217   0.8351   0.0160
  -3.500  -0.2625   0.01088   0.00377  -0.0215   0.8343   0.0242
  -3.250  -0.2358   0.01063   0.00355  -0.0214   0.8334   0.0401
  -3.000  -0.2093   0.01029   0.00334  -0.0213   0.8324   0.0724
  -2.750  -0.1827   0.00996   0.00315  -0.0213   0.8312   0.1138
  -2.500  -0.1569   0.00950   0.00300  -0.0212   0.8299   0.1902
  -2.250  -0.1317   0.00900   0.00287  -0.0210   0.8282   0.2884
  -2.000  -0.1066   0.00853   0.00276  -0.0208   0.8260   0.3888
  -1.750  -0.0817   0.00812   0.00266  -0.0204   0.8236   0.4806
  -1.500  -0.0574   0.00770   0.00256  -0.0199   0.8211   0.5804
  -1.250  -0.0353   0.00708   0.00248  -0.0187   0.8179   0.7171
  -1.000  -0.0164   0.00704   0.00288  -0.0160   0.8144   0.8421
  -0.750   0.0106   0.00711   0.00290  -0.0156   0.8112   0.8664
  -0.500   0.0373   0.00719   0.00291  -0.0152   0.8084   0.8786
  -0.250   0.0643   0.00720   0.00291  -0.0149   0.8042   0.8877
   0.000   0.0902   0.00720   0.00291  -0.0142   0.7996   0.8944
   0.250   0.1169   0.00718   0.00285  -0.0137   0.7955   0.9009
   0.500   0.1426   0.00712   0.00283  -0.0130   0.7890   0.9064
   0.750   0.1683   0.00707   0.00277  -0.0123   0.7835   0.9133
   1.000   0.1936   0.00701   0.00276  -0.0115   0.7759   0.9190
   1.250   0.2188   0.00696   0.00274  -0.0107   0.7669   0.9254
   1.500   0.2436   0.00688   0.00271  -0.0098   0.7548   0.9317
   1.750   0.2674   0.00673   0.00258  -0.0085   0.7358   0.9387
   2.000   0.2910   0.00648   0.00216  -0.0071   0.6961   0.9436
   2.250   0.3134   0.00665   0.00201  -0.0057   0.6270   0.9459
   2.500   0.3365   0.00702   0.00208  -0.0049   0.5564   0.9471
   2.750   0.3602   0.00739   0.00221  -0.0043   0.4911   0.9483
   3.000   0.3843   0.00778   0.00235  -0.0039   0.4277   0.9492
   3.250   0.4086   0.00817   0.00249  -0.0035   0.3650   0.9500
   3.500   0.4335   0.00852   0.00265  -0.0033   0.3144   0.9509
   3.750   0.4585   0.00887   0.00282  -0.0031   0.2679   0.9520
   4.000   0.4839   0.00922   0.00302  -0.0029   0.2254   0.9527
   4.250   0.5094   0.00957   0.00322  -0.0028   0.1877   0.9534
   4.500   0.5353   0.00987   0.00342  -0.0028   0.1600   0.9541
   4.750   0.5611   0.01020   0.00365  -0.0027   0.1318   0.9547
   5.250   0.6125   0.01084   0.00417  -0.0025   0.0898   0.9561
   5.500   0.6380   0.01115   0.00444  -0.0023   0.0748   0.9571
   5.750   0.6636   0.01148   0.00475  -0.0022   0.0620   0.9578
   6.000   0.6889   0.01185   0.00508  -0.0020   0.0485   0.9586
   6.250   0.7141   0.01223   0.00542  -0.0019   0.0367   0.9594
   6.500   0.7396   0.01257   0.00578  -0.0017   0.0309   0.9602
   6.750   0.7649   0.01295   0.00621  -0.0016   0.0252   0.9611
   7.000   0.7897   0.01338   0.00665  -0.0013   0.0189   0.9621
   7.250   0.8142   0.01386   0.00714  -0.0011   0.0129   0.9631
   7.500   0.8379   0.01444   0.00775  -0.0007   0.0091   0.9643
   7.750   0.8617   0.01503   0.00839  -0.0003   0.0074   0.9656
   8.000   0.8842   0.01580   0.00924   0.0002   0.0056   0.9670
   8.250   0.9083   0.01629   0.00982   0.0005   0.0048   0.9684
   8.500   0.9317   0.01699   0.01063   0.0008   0.0041   0.9703
   8.750   0.9551   0.01775   0.01152   0.0010   0.0036   0.9723
   9.000   0.9751   0.01908   0.01303   0.0016   0.0031   0.9750
   9.250   0.9975   0.02007   0.01416   0.0019   0.0029   0.9778
   9.500   1.0199   0.02108   0.01533   0.0020   0.0027   0.9811
   9.750   1.0415   0.02235   0.01679   0.0022   0.0024   0.9871
  10.000   1.0598   0.02371   0.01835   0.0028   0.0023   1.0000
  10.250   1.0748   0.02518   0.02002   0.0039   0.0021   1.0000
  10.500   1.0879   0.02677   0.02182   0.0052   0.0020   1.0000
  10.750   1.0988   0.02843   0.02369   0.0066   0.0019   1.0000
  11.000   1.1047   0.03020   0.02567   0.0087   0.0019   1.0000
  11.250   1.1050   0.03224   0.02794   0.0112   0.0019   1.0000
  11.500   1.1050   0.03424   0.03014   0.0131   0.0018   1.0000
  11.750   1.1006   0.03676   0.03288   0.0150   0.0018   1.0000
  12.000   1.0947   0.03948   0.03584   0.0164   0.0018   1.0000
  12.250   1.0840   0.04284   0.03943   0.0175   0.0017   1.0000
  12.500   1.0733   0.04641   0.04318   0.0179   0.0017   1.0000
  12.750   1.0553   0.05136   0.04838   0.0171   0.0018   1.0000
  13.000   1.0374   0.05711   0.05433   0.0145   0.0018   1.0000
  13.250   1.0166   0.06479   0.06221   0.0095   0.0018   1.0000
  13.500   0.9930   0.07522   0.07280   0.0018   0.0018   1.0000
  13.750   0.9586   0.08988   0.08766  -0.0076   0.0019   1.0000
  14.000   0.9194   0.10508   0.10297  -0.0159   0.0020   1.0000
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