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S1046 17% (Danny Howell) (s1046-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S1046 17% (Danny Howell) (s1046-il)
Reynolds number: 50,000
Max Cl/Cd: 25.26 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1046-il-50000-n5.txt
Download as CSV file: xf-s1046-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1046 17% (Danny Howell)                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7741   0.09729   0.08941  -0.0179   1.0000   0.1560
 -13.750  -0.7288   0.10260   0.09460  -0.0141   1.0000   0.1600
 -13.500  -0.8718   0.07414   0.06614  -0.0291   1.0000   0.1692
 -13.250  -0.7606   0.08953   0.08150  -0.0196   1.0000   0.1752
 -13.000  -0.8876   0.06629   0.05817  -0.0313   1.0000   0.1829
 -12.750  -0.8308   0.07159   0.06352  -0.0274   1.0000   0.1910
 -12.500  -0.9037   0.05908   0.05081  -0.0327   1.0000   0.1971
 -12.250  -0.8792   0.05958   0.05135  -0.0314   1.0000   0.2053
 -12.000  -0.9183   0.05287   0.04445  -0.0329   1.0000   0.2118
 -11.750  -0.9011   0.05242   0.04402  -0.0320   1.0000   0.2201
 -11.500  -0.9280   0.04791   0.03932  -0.0318   1.0000   0.2270
 -11.250  -0.9114   0.04743   0.03887  -0.0307   1.0000   0.2355
 -11.000  -0.9346   0.04398   0.03523  -0.0290   1.0000   0.2429
 -10.750  -0.9146   0.04374   0.03505  -0.0279   1.0000   0.2516
 -10.500  -0.9346   0.04114   0.03226  -0.0248   1.0000   0.2592
 -10.250  -0.9126   0.04098   0.03213  -0.0236   1.0000   0.2680
 -10.000  -0.9148   0.03942   0.03045  -0.0212   1.0000   0.2766
  -9.750  -0.9022   0.03868   0.02967  -0.0195   1.0000   0.2857
  -9.500  -0.8915   0.03775   0.02868  -0.0178   1.0000   0.2944
  -9.250  -0.8871   0.03653   0.02732  -0.0156   1.0000   0.3041
  -9.000  -0.8669   0.03616   0.02697  -0.0144   1.0000   0.3128
  -8.750  -0.8617   0.03494   0.02560  -0.0121   1.0000   0.3224
  -8.500  -0.8423   0.03456   0.02523  -0.0108   1.0000   0.3315
  -8.250  -0.8303   0.03375   0.02435  -0.0090   1.0000   0.3406
  -8.000  -0.8186   0.03300   0.02352  -0.0070   1.0000   0.3502
  -7.750  -0.8015   0.03257   0.02310  -0.0054   1.0000   0.3588
  -7.500  -0.7963   0.03158   0.02196  -0.0028   1.0000   0.3687
  -7.250  -0.7766   0.03140   0.02186  -0.0013   1.0000   0.3765
  -7.000  -0.7705   0.03064   0.02102   0.0014   1.0000   0.3859
  -6.750  -0.7569   0.03036   0.02078   0.0036   1.0000   0.3938
  -6.500  -0.7522   0.02979   0.02013   0.0066   1.0000   0.4027
  -6.250  -0.7431   0.02951   0.01986   0.0093   1.0000   0.4106
  -6.000  -0.7333   0.02907   0.01935   0.0113   0.9982   0.4195
  -5.750  -0.6951   0.02861   0.01875   0.0083   0.9838   0.4326
  -5.500  -0.6542   0.02850   0.01862   0.0057   0.9710   0.4432
  -5.250  -0.6153   0.02823   0.01829   0.0031   0.9577   0.4548
  -5.000  -0.5777   0.02786   0.01781   0.0007   0.9447   0.4671
  -4.750  -0.5386   0.02754   0.01738  -0.0019   0.9328   0.4797
  -4.500  -0.4958   0.02742   0.01726  -0.0046   0.9222   0.4903
  -4.250  -0.4609   0.02718   0.01695  -0.0060   0.9088   0.5018
  -4.000  -0.4285   0.02687   0.01655  -0.0072   0.8954   0.5141
  -3.750  -0.3934   0.02677   0.01644  -0.0083   0.8829   0.5246
  -3.500  -0.3593   0.02662   0.01624  -0.0093   0.8707   0.5355
  -3.250  -0.3298   0.02639   0.01594  -0.0096   0.8577   0.5474
  -3.000  -0.3021   0.02630   0.01581  -0.0094   0.8438   0.5583
  -2.750  -0.2742   0.02624   0.01574  -0.0091   0.8304   0.5684
  -2.500  -0.2486   0.02609   0.01553  -0.0086   0.8174   0.5802
  -2.250  -0.2218   0.02600   0.01537  -0.0081   0.8052   0.5917
  -2.000  -0.1947   0.02598   0.01535  -0.0074   0.7926   0.6017
  -1.750  -0.1717   0.02590   0.01524  -0.0064   0.7792   0.6133
  -1.500  -0.1488   0.02581   0.01510  -0.0054   0.7664   0.6256
  -1.250  -0.1217   0.02584   0.01513  -0.0047   0.7546   0.6355
  -1.000  -0.0968   0.02577   0.01503  -0.0038   0.7429   0.6472
  -0.750  -0.0753   0.02571   0.01494  -0.0026   0.7298   0.6598
  -0.500  -0.0495   0.02577   0.01501  -0.0018   0.7175   0.6704
  -0.250  -0.0236   0.02573   0.01496  -0.0010   0.7064   0.6818
   0.000   0.0000   0.02569   0.01491   0.0000   0.6944   0.6944
   0.250   0.0236   0.02573   0.01496   0.0010   0.6818   0.7064
   0.500   0.0494   0.02577   0.01501   0.0018   0.6704   0.7175
   0.750   0.0753   0.02571   0.01494   0.0026   0.6599   0.7297
   1.000   0.0968   0.02576   0.01502   0.0038   0.6472   0.7429
   1.250   0.1217   0.02583   0.01512   0.0047   0.6355   0.7546
   1.500   0.1488   0.02581   0.01509   0.0054   0.6256   0.7664
   1.750   0.1717   0.02590   0.01524   0.0064   0.6133   0.7792
   2.000   0.1947   0.02598   0.01535   0.0074   0.6017   0.7926
   2.250   0.2218   0.02599   0.01537   0.0081   0.5917   0.8052
   2.500   0.2486   0.02609   0.01553   0.0086   0.5802   0.8174
   2.750   0.2741   0.02624   0.01574   0.0091   0.5685   0.8305
   3.000   0.3021   0.02630   0.01580   0.0094   0.5583   0.8438
   3.250   0.3298   0.02639   0.01594   0.0096   0.5474   0.8577
   3.500   0.3593   0.02662   0.01624   0.0093   0.5356   0.8707
   3.750   0.3934   0.02677   0.01644   0.0083   0.5247   0.8829
   4.000   0.4285   0.02686   0.01655   0.0072   0.5141   0.8954
   4.250   0.4610   0.02717   0.01695   0.0060   0.5018   0.9088
   4.500   0.4958   0.02742   0.01726   0.0046   0.4904   0.9222
   4.750   0.5385   0.02754   0.01738   0.0019   0.4797   0.9329
   5.000   0.5778   0.02785   0.01780  -0.0007   0.4670   0.9448
   5.250   0.6155   0.02822   0.01828  -0.0031   0.4547   0.9578
   5.500   0.6543   0.02850   0.01862  -0.0057   0.4431   0.9710
   5.750   0.6952   0.02860   0.01874  -0.0083   0.4326   0.9838
   6.000   0.7334   0.02907   0.01935  -0.0114   0.4195   0.9983
   6.250   0.7430   0.02951   0.01986  -0.0092   0.4106   1.0000
   6.500   0.7521   0.02978   0.02013  -0.0066   0.4026   1.0000
   6.750   0.7568   0.03036   0.02078  -0.0036   0.3938   1.0000
   7.000   0.7704   0.03064   0.02101  -0.0014   0.3859   1.0000
   7.250   0.7766   0.03140   0.02186   0.0013   0.3766   1.0000
   7.500   0.7963   0.03157   0.02195   0.0028   0.3687   1.0000
   7.750   0.8015   0.03256   0.02309   0.0054   0.3588   1.0000
   8.000   0.8186   0.03300   0.02352   0.0070   0.3502   1.0000
   8.250   0.8303   0.03375   0.02435   0.0090   0.3406   1.0000
   8.500   0.8424   0.03456   0.02522   0.0108   0.3315   1.0000
   8.750   0.8619   0.03494   0.02559   0.0121   0.3224   1.0000
   9.000   0.8671   0.03615   0.02696   0.0144   0.3128   1.0000
   9.250   0.8873   0.03653   0.02731   0.0155   0.3041   1.0000
   9.500   0.8917   0.03776   0.02869   0.0178   0.2944   1.0000
   9.750   0.9025   0.03868   0.02967   0.0195   0.2856   1.0000
  10.000   0.9152   0.03940   0.03043   0.0211   0.2765   1.0000
  10.250   0.9131   0.04097   0.03213   0.0236   0.2680   1.0000
  10.500   0.9354   0.04113   0.03225   0.0247   0.2592   1.0000
  10.750   0.9153   0.04373   0.03504   0.0278   0.2515   1.0000
  11.000   0.9347   0.04400   0.03526   0.0290   0.2428   1.0000
  11.250   0.9123   0.04740   0.03885   0.0306   0.2355   1.0000
  11.500   0.9287   0.04789   0.03931   0.0317   0.2270   1.0000
  11.750   0.9025   0.05234   0.04395   0.0319   0.2199   1.0000
  12.000   0.9184   0.05292   0.04450   0.0328   0.2117   1.0000
  12.250   0.8814   0.05940   0.05116   0.0314   0.2051   1.0000
  12.500   0.9037   0.05917   0.05090   0.0325   0.1969   1.0000
  12.750   0.8338   0.07128   0.06321   0.0275   0.1909   1.0000
  13.000   0.8877   0.06641   0.05830   0.0311   0.1829   1.0000
  13.250   0.7630   0.08930   0.08129   0.0195   0.1752   1.0000
  13.500   0.8709   0.07443   0.06643   0.0287   0.1691   1.0000
  13.750   0.7309   0.10244   0.09444   0.0140   0.1600   1.0000
  14.000   0.7810   0.09619   0.08831   0.0183   0.1559   1.0000
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