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S1046 17% (Danny Howell) (s1046-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S1046 17% (Danny Howell) (s1046-il)
Reynolds number: 50,000
Max Cl/Cd: 16.23 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1046-il-50000.txt
Download as CSV file: xf-s1046-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.5247   0.15249   0.14428   0.0170   1.0000   0.3522
 -13.250  -0.4975   0.14704   0.13873   0.0165   1.0000   0.3620
 -13.000  -0.5040   0.14489   0.13659   0.0156   1.0000   0.3702
 -12.750  -0.4866   0.14116   0.13278   0.0151   1.0000   0.3811
 -12.500  -0.4773   0.13757   0.12915   0.0144   1.0000   0.3896
 -12.250  -0.4929   0.13699   0.12859   0.0141   1.0000   0.4002
 -12.000  -0.4598   0.13142   0.12291   0.0133   1.0000   0.4103
 -11.750  -0.4597   0.12867   0.12013   0.0127   1.0000   0.4193
 -11.500  -0.4637   0.12718   0.11863   0.0128   1.0000   0.4318
 -11.250  -0.4350   0.12232   0.11367   0.0119   1.0000   0.4415
 -11.000  -0.4382   0.11989   0.11123   0.0116   1.0000   0.4507
 -10.750  -0.4381   0.11811   0.10943   0.0118   1.0000   0.4639
 -10.500  -0.4094   0.11367   0.10491   0.0108   1.0000   0.4749
 -10.250  -0.4091   0.11102   0.10223   0.0106   1.0000   0.4835
 -10.000  -0.4139   0.10964   0.10084   0.0112   1.0000   0.4964
  -9.750  -0.3851   0.10561   0.09673   0.0102   1.0000   0.5095
  -9.500  -0.3762   0.10253   0.09362   0.0098   1.0000   0.5172
  -9.250  -0.3874   0.10144   0.09254   0.0108   1.0000   0.5289
  -9.000  -0.4390   0.09106   0.08215   0.0039   1.0000   0.4470
  -8.750  -0.4327   0.08704   0.07808   0.0027   1.0000   0.4439
  -8.500  -0.4368   0.08313   0.07416   0.0018   1.0000   0.4433
  -8.250  -0.4478   0.07920   0.07024   0.0012   1.0000   0.4455
  -8.000  -0.4708   0.07456   0.06564   0.0006   1.0000   0.4477
  -7.750  -0.4360   0.07374   0.06474   0.0012   1.0000   0.4594
  -7.500  -0.4644   0.06914   0.06020   0.0012   1.0000   0.4636
  -7.250  -0.4296   0.06841   0.05940   0.0016   1.0000   0.4741
  -7.000  -0.4646   0.06372   0.05482   0.0024   1.0000   0.4797
  -6.750  -0.4266   0.06336   0.05438   0.0028   1.0000   0.4903
  -6.500  -0.4836   0.05793   0.04914   0.0052   1.0000   0.4963
  -6.250  -0.4303   0.05854   0.04964   0.0050   1.0000   0.5069
  -6.000  -0.5366   0.05179   0.04324   0.0120   1.0000   0.5127
  -5.750  -0.4586   0.05386   0.04516   0.0105   1.0000   0.5232
  -5.500  -0.5914   0.04771   0.03933   0.0222   1.0000   0.5280
  -5.250  -0.5667   0.04833   0.03995   0.0244   1.0000   0.5358
  -5.000  -0.6425   0.04359   0.03522   0.0317   1.0000   0.5455
  -4.750  -0.6158   0.04451   0.03616   0.0337   1.0000   0.5532
  -4.500  -0.6394   0.04201   0.03360   0.0374   1.0000   0.5638
  -4.250  -0.6359   0.04133   0.03290   0.0400   1.0000   0.5739
  -4.000  -0.6311   0.04067   0.03223   0.0424   1.0000   0.5839
  -3.750  -0.6349   0.03914   0.03062   0.0446   1.0000   0.5958
  -3.500  -0.6270   0.03865   0.03011   0.0466   1.0000   0.6067
  -3.250  -0.6140   0.03835   0.02979   0.0480   0.9989   0.6176
  -3.000  -0.5636   0.03853   0.02988   0.0428   0.9843   0.6329
  -2.750  -0.5158   0.03867   0.02995   0.0382   0.9698   0.6483
  -2.500  -0.4717   0.03866   0.02986   0.0343   0.9552   0.6634
  -2.250  -0.4308   0.03864   0.02979   0.0311   0.9405   0.6787
  -2.000  -0.3928   0.03855   0.02963   0.0284   0.9258   0.6939
  -1.750  -0.3566   0.03850   0.02953   0.0261   0.9111   0.7093
  -1.500  -0.3131   0.03875   0.02975   0.0234   0.8966   0.7235
  -1.250  -0.2659   0.03907   0.03006   0.0203   0.8824   0.7377
  -1.000  -0.2151   0.03929   0.03026   0.0166   0.8683   0.7523
  -0.750  -0.1478   0.03953   0.03048   0.0104   0.8550   0.7675
  -0.500  -0.0811   0.03962   0.03055   0.0044   0.8411   0.7824
  -0.250  -0.0398   0.03963   0.03056   0.0021   0.8263   0.7969
   0.000   0.0002   0.03963   0.03055   0.0000   0.8115   0.8115
   0.250   0.0396   0.03964   0.03056  -0.0021   0.7969   0.8263
   0.500   0.0818   0.03962   0.03055  -0.0045   0.7824   0.8412
   0.750   0.1478   0.03953   0.03048  -0.0104   0.7676   0.8550
   1.000   0.2151   0.03929   0.03026  -0.0166   0.7523   0.8682
   1.250   0.2659   0.03906   0.03006  -0.0203   0.7377   0.8824
   1.500   0.3132   0.03873   0.02974  -0.0234   0.7236   0.8966
   1.750   0.3563   0.03849   0.02953  -0.0261   0.7093   0.9111
   2.000   0.3925   0.03854   0.02962  -0.0283   0.6939   0.9257
   2.250   0.4304   0.03864   0.02979  -0.0311   0.6787   0.9404
   2.500   0.4718   0.03866   0.02986  -0.0343   0.6634   0.9552
   2.750   0.5159   0.03866   0.02994  -0.0383   0.6483   0.9698
   3.000   0.5636   0.03852   0.02987  -0.0428   0.6329   0.9843
   3.250   0.6140   0.03833   0.02978  -0.0480   0.6176   0.9989
   3.500   0.6270   0.03863   0.03008  -0.0466   0.6068   1.0000
   3.750   0.6346   0.03915   0.03063  -0.0446   0.5959   1.0000
   4.000   0.6312   0.04064   0.03220  -0.0424   0.5838   1.0000
   4.250   0.6358   0.04132   0.03289  -0.0400   0.5739   1.0000
   4.500   0.6390   0.04203   0.03363  -0.0374   0.5638   1.0000
   4.750   0.6160   0.04448   0.03613  -0.0337   0.5532   1.0000
   5.000   0.6428   0.04355   0.03518  -0.0317   0.5455   1.0000
   5.250   0.5672   0.04829   0.03990  -0.0244   0.5357   1.0000
   5.500   0.5920   0.04767   0.03929  -0.0222   0.5280   1.0000
   5.750   0.4593   0.05382   0.04512  -0.0105   0.5232   1.0000
   6.000   0.5378   0.05172   0.04317  -0.0121   0.5128   1.0000
   6.250   0.4306   0.05853   0.04963  -0.0051   0.5069   1.0000
   6.500   0.4823   0.05799   0.04918  -0.0051   0.4963   1.0000
   6.750   0.4270   0.06337   0.05439  -0.0029   0.4903   1.0000
   7.000   0.4643   0.06373   0.05483  -0.0024   0.4796   1.0000
   7.250   0.4302   0.06839   0.05938  -0.0017   0.4741   1.0000
   7.500   0.4644   0.06915   0.06021  -0.0012   0.4635   1.0000
   7.750   0.4365   0.07370   0.06471  -0.0012   0.4591   1.0000
   8.000   0.4707   0.07456   0.06564  -0.0007   0.4476   1.0000
   8.250   0.4485   0.07919   0.07022  -0.0013   0.4455   1.0000
   8.500   0.4375   0.08312   0.07415  -0.0019   0.4432   1.0000
   8.750   0.4331   0.08703   0.07807  -0.0028   0.4436   1.0000
   9.000   0.4393   0.09102   0.08211  -0.0040   0.4469   1.0000
   9.250   0.3886   0.10143   0.09253  -0.0110   0.5289   1.0000
   9.500   0.3769   0.10250   0.09359  -0.0100   0.5174   1.0000
   9.750   0.3857   0.10557   0.09669  -0.0104   0.5093   1.0000
  10.000   0.4141   0.10957   0.10076  -0.0113   0.4963   1.0000
  10.250   0.4117   0.11112   0.10234  -0.0108   0.4832   1.0000
  10.500   0.4105   0.11367   0.10491  -0.0110   0.4748   1.0000
  10.750   0.4399   0.11821   0.10953  -0.0120   0.4640   1.0000
  11.000   0.4399   0.11995   0.11130  -0.0118   0.4506   1.0000
  11.250   0.4362   0.12234   0.11370  -0.0120   0.4416   1.0000
  11.500   0.4655   0.12724   0.11869  -0.0130   0.4319   1.0000
  11.750   0.4617   0.12875   0.12021  -0.0129   0.4191   1.0000
  12.000   0.4610   0.13144   0.12293  -0.0135   0.4101   1.0000
  12.250   0.4942   0.13702   0.12862  -0.0143   0.4002   1.0000
  12.500   0.4791   0.13764   0.12922  -0.0146   0.3893   1.0000
  12.750   0.4882   0.14124   0.13287  -0.0153   0.3812   1.0000
  13.000   0.5058   0.14502   0.13672  -0.0158   0.3701   1.0000
  13.250   0.4989   0.14709   0.13879  -0.0167   0.3620   1.0000
  13.500   0.5256   0.15252   0.14432  -0.0172   0.3521   1.0000
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