Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD5060 (9.5%) (sd5060-il)
Reynolds number: 200,000
Max Cl/Cd: 68.64 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd5060-il-200000.txt
Download as CSV file: xf-sd5060-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD5060 (9.5%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4717   0.09617   0.09270  -0.0147   1.0000   0.0642
  -9.000  -0.4952   0.09010   0.08676  -0.0250   1.0000   0.0666
  -8.750  -0.5048   0.08461   0.08133  -0.0310   1.0000   0.0668
  -8.500  -0.4921   0.08074   0.07748  -0.0265   1.0000   0.0684
  -8.250  -0.4825   0.07824   0.07499  -0.0257   1.0000   0.0695
  -8.000  -0.4795   0.07514   0.07193  -0.0265   1.0000   0.0709
  -7.750  -0.4808   0.07106   0.06790  -0.0297   1.0000   0.0723
  -7.500  -0.5435   0.04115   0.03703  -0.0528   1.0000   0.0409
  -7.250  -0.5529   0.03150   0.02626  -0.0526   1.0000   0.0358
  -7.000  -0.5426   0.02834   0.02258  -0.0508   1.0000   0.0351
  -6.750  -0.5309   0.02598   0.01990  -0.0488   1.0000   0.0353
  -6.500  -0.5177   0.02438   0.01817  -0.0470   1.0000   0.0364
  -6.250  -0.5030   0.02326   0.01693  -0.0453   1.0000   0.0380
  -6.000  -0.4871   0.02184   0.01527  -0.0436   1.0000   0.0390
  -5.750  -0.4698   0.02041   0.01361  -0.0421   1.0000   0.0397
  -5.500  -0.4338   0.01887   0.01181  -0.0439   0.9961   0.0412
  -5.250  -0.3950   0.01777   0.01050  -0.0461   0.9912   0.0432
  -5.000  -0.3579   0.01623   0.00898  -0.0483   0.9862   0.0476
  -4.750  -0.3182   0.01533   0.00801  -0.0508   0.9815   0.0524
  -4.500  -0.2813   0.01431   0.00698  -0.0528   0.9752   0.0610
  -4.250  -0.2405   0.01316   0.00608  -0.0556   0.9710   0.1090
  -4.000  -0.2031   0.01274   0.00580  -0.0578   0.9644   0.1576
  -3.750  -0.1623   0.01247   0.00555  -0.0605   0.9591   0.1926
  -3.500  -0.1250   0.01220   0.00539  -0.0625   0.9528   0.2279
  -3.250  -0.0895   0.01193   0.00520  -0.0640   0.9453   0.2622
  -3.000  -0.0565   0.01167   0.00500  -0.0649   0.9374   0.2967
  -2.750  -0.0251   0.01135   0.00481  -0.0655   0.9292   0.3322
  -2.500   0.0023   0.01108   0.00468  -0.0652   0.9192   0.3745
  -2.250   0.0295   0.01078   0.00456  -0.0648   0.9104   0.4269
  -2.000   0.0544   0.01048   0.00448  -0.0638   0.9002   0.4887
  -1.750   0.0781   0.01019   0.00444  -0.0626   0.8895   0.5589
  -1.500   0.1012   0.00990   0.00440  -0.0610   0.8800   0.6374
  -1.250   0.1229   0.00961   0.00437  -0.0590   0.8700   0.7203
  -1.000   0.1432   0.00938   0.00438  -0.0565   0.8590   0.8058
  -0.750   0.1681   0.00919   0.00432  -0.0546   0.8494   0.8935
  -0.500   0.2149   0.00900   0.00409  -0.0576   0.8404   0.9705
  -0.250   0.2543   0.00894   0.00392  -0.0598   0.8289   1.0000
   0.000   0.2777   0.00897   0.00384  -0.0587   0.8169   1.0000
   0.250   0.3019   0.00900   0.00375  -0.0576   0.8049   1.0000
   0.500   0.3265   0.00903   0.00366  -0.0566   0.7928   1.0000
   0.750   0.3516   0.00906   0.00359  -0.0557   0.7797   1.0000
   1.000   0.3771   0.00910   0.00354  -0.0549   0.7658   1.0000
   1.250   0.4029   0.00914   0.00350  -0.0542   0.7517   1.0000
   1.500   0.4289   0.00919   0.00348  -0.0535   0.7373   1.0000
   1.750   0.4551   0.00924   0.00347  -0.0528   0.7224   1.0000
   2.000   0.4813   0.00931   0.00346  -0.0522   0.7070   1.0000
   2.250   0.5076   0.00938   0.00345  -0.0516   0.6909   1.0000
   2.500   0.5340   0.00946   0.00348  -0.0510   0.6732   1.0000
   2.750   0.5604   0.00955   0.00353  -0.0505   0.6542   1.0000
   3.000   0.5867   0.00966   0.00356  -0.0499   0.6347   1.0000
   3.250   0.6130   0.00979   0.00362  -0.0493   0.6142   1.0000
   3.500   0.6392   0.00993   0.00372  -0.0488   0.5911   1.0000
   3.750   0.6653   0.01010   0.00382  -0.0482   0.5668   1.0000
   4.000   0.6911   0.01030   0.00393  -0.0477   0.5404   1.0000
   4.250   0.7167   0.01054   0.00408  -0.0471   0.5114   1.0000
   4.500   0.7420   0.01082   0.00427  -0.0465   0.4783   1.0000
   4.750   0.7667   0.01117   0.00448  -0.0459   0.4428   1.0000
   5.000   0.7912   0.01157   0.00475  -0.0453   0.4047   1.0000
   5.250   0.8149   0.01207   0.00508  -0.0446   0.3647   1.0000
   5.500   0.8384   0.01263   0.00546  -0.0440   0.3259   1.0000
   5.750   0.8616   0.01324   0.00590  -0.0434   0.2925   1.0000
   6.000   0.8848   0.01387   0.00638  -0.0428   0.2632   1.0000
   6.250   0.9082   0.01449   0.00691  -0.0422   0.2386   1.0000
   6.500   0.9313   0.01514   0.00747  -0.0416   0.2185   1.0000
   6.750   0.9547   0.01576   0.00804  -0.0410   0.2009   1.0000
   7.000   0.9778   0.01640   0.00864  -0.0404   0.1861   1.0000
   7.250   1.0008   0.01705   0.00929  -0.0398   0.1729   1.0000
   7.500   1.0235   0.01774   0.00994  -0.0391   0.1610   1.0000
   7.750   1.0455   0.01850   0.01064  -0.0384   0.1500   1.0000
   8.000   1.0687   0.01902   0.01126  -0.0378   0.1394   1.0000
   8.250   1.0908   0.01974   0.01203  -0.0371   0.1296   1.0000
   8.500   1.1119   0.02056   0.01285  -0.0363   0.1203   1.0000
   8.750   1.1332   0.02123   0.01357  -0.0355   0.1111   1.0000
   9.000   1.1539   0.02201   0.01444  -0.0346   0.1020   1.0000
   9.250   1.1730   0.02297   0.01541  -0.0337   0.0937   1.0000
   9.500   1.1923   0.02368   0.01618  -0.0327   0.0853   1.0000
   9.750   1.2105   0.02461   0.01725  -0.0316   0.0771   1.0000
  10.000   1.2264   0.02567   0.01828  -0.0304   0.0696   1.0000
  10.250   1.2434   0.02630   0.01905  -0.0292   0.0622   1.0000
  10.500   1.2570   0.02749   0.02032  -0.0277   0.0557   1.0000
  10.750   1.2689   0.02852   0.02138  -0.0261   0.0499   1.0000
  11.000   1.2775   0.02987   0.02287  -0.0240   0.0446   1.0000
  11.250   1.2833   0.03109   0.02412  -0.0219   0.0401   1.0000
  11.500   1.2867   0.03303   0.02621  -0.0197   0.0363   1.0000
  11.750   1.2910   0.03465   0.02795  -0.0179   0.0329   1.0000
  12.000   1.2903   0.03718   0.03046  -0.0161   0.0304   1.0000
  12.250   1.2928   0.03946   0.03297  -0.0147   0.0286   1.0000
  12.500   1.2944   0.04173   0.03542  -0.0136   0.0267   1.0000
  12.750   1.2953   0.04393   0.03770  -0.0130   0.0250   1.0000
  13.000   1.2947   0.04672   0.04056  -0.0124   0.0240   1.0000
  13.250   1.2893   0.05054   0.04452  -0.0119   0.0229   1.0000
  13.500   1.2854   0.05386   0.04808  -0.0120   0.0223   1.0000
  13.750   1.2796   0.05767   0.05212  -0.0125   0.0218   1.0000
  14.000   1.2719   0.06191   0.05659  -0.0134   0.0214   1.0000
  14.250   1.2620   0.06662   0.06152  -0.0149   0.0210   1.0000
  14.500   1.2504   0.07181   0.06692  -0.0169   0.0207   1.0000
  14.750   1.2367   0.07763   0.07296  -0.0196   0.0206   1.0000
  15.000   1.2210   0.08412   0.07966  -0.0230   0.0205   1.0000
  15.250   1.2028   0.09154   0.08730  -0.0272   0.0205   1.0000
  15.500   1.1818   0.10000   0.09597  -0.0324   0.0206   1.0000
  15.750   1.1573   0.10985   0.10604  -0.0387   0.0209   1.0000
  16.000   1.1296   0.12116   0.11756  -0.0461   0.0214   1.0000
  16.250   1.0972   0.13447   0.13105  -0.0549   0.0219   1.0000
  16.500   1.0604   0.14989   0.14659  -0.0646   0.0227   1.0000
<< Back to SD5060 (9.5%) (sd5060-il)

Polar data table (+)

Polar graphs


<< Back to SD5060 (9.5%) (sd5060-il)