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SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD7003-085-88 (sd7003-il)
Reynolds number: 50,000
Max Cl/Cd: 32.72 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7003-il-50000-n5.txt
Download as CSV file: xf-sd7003-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7003-085-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5626   0.09336   0.08630  -0.0130   1.0000   0.0482
  -9.000  -0.5667   0.08775   0.08076  -0.0166   1.0000   0.0482
  -8.750  -0.5706   0.08217   0.07524  -0.0203   1.0000   0.0480
  -8.500  -0.5765   0.07658   0.06970  -0.0243   1.0000   0.0478
  -8.250  -0.5826   0.07102   0.06410  -0.0279   1.0000   0.0477
  -8.000  -0.5875   0.06550   0.05848  -0.0310   1.0000   0.0476
  -7.750  -0.5902   0.05998   0.05274  -0.0335   1.0000   0.0476
  -7.500  -0.5893   0.05456   0.04698  -0.0354   1.0000   0.0478
  -7.250  -0.5839   0.04941   0.04141  -0.0365   1.0000   0.0484
  -7.000  -0.5688   0.04719   0.03921  -0.0363   1.0000   0.0510
  -6.750  -0.5546   0.04406   0.03578  -0.0364   1.0000   0.0546
  -6.500  -0.5398   0.03986   0.03094  -0.0367   1.0000   0.0577
  -6.250  -0.5217   0.03607   0.02651  -0.0365   1.0000   0.0607
  -6.000  -0.5013   0.03433   0.02471  -0.0360   1.0000   0.0663
  -5.750  -0.4790   0.03156   0.02128  -0.0354   1.0000   0.0718
  -5.500  -0.4571   0.02976   0.01942  -0.0348   1.0000   0.0783
  -5.250  -0.4334   0.02787   0.01710  -0.0340   1.0000   0.0866
  -5.000  -0.4106   0.02647   0.01567  -0.0332   1.0000   0.0958
  -4.750  -0.3873   0.02508   0.01419  -0.0323   1.0000   0.1059
  -4.500  -0.3640   0.02390   0.01290  -0.0315   1.0000   0.1190
  -4.250  -0.3406   0.02279   0.01172  -0.0305   1.0000   0.1328
  -4.000  -0.3174   0.02183   0.01075  -0.0297   1.0000   0.1515
  -3.750  -0.2936   0.02087   0.00980  -0.0289   1.0000   0.1733
  -3.500  -0.2708   0.01997   0.00901  -0.0282   1.0000   0.2043
  -3.250  -0.2481   0.01907   0.00832  -0.0274   1.0000   0.2477
  -3.000  -0.2261   0.01819   0.00778  -0.0267   1.0000   0.3153
  -2.750  -0.2053   0.01735   0.00741  -0.0255   1.0000   0.4093
  -2.500  -0.1869   0.01663   0.00721  -0.0235   1.0000   0.5224
  -2.250  -0.1713   0.01613   0.00719  -0.0202   1.0000   0.6381
  -2.000  -0.1569   0.01581   0.00716  -0.0164   1.0000   0.7432
  -1.750  -0.1380   0.01557   0.00707  -0.0133   1.0000   0.8431
  -1.500  -0.0846   0.01534   0.00672  -0.0174   1.0000   0.9652
  -1.250  -0.0567   0.01528   0.00644  -0.0184   1.0000   1.0000
  -1.000  -0.0397   0.01534   0.00631  -0.0174   1.0000   1.0000
  -0.750  -0.0218   0.01546   0.00627  -0.0165   1.0000   1.0000
  -0.500   0.0129   0.01567   0.00630  -0.0188   0.9896   1.0000
  -0.250   0.0626   0.01590   0.00637  -0.0236   0.9699   1.0000
   0.000   0.1090   0.01604   0.00639  -0.0276   0.9479   1.0000
   0.250   0.1581   0.01615   0.00641  -0.0317   0.9276   1.0000
   0.500   0.2008   0.01621   0.00641  -0.0345   0.9030   1.0000
   0.750   0.2422   0.01626   0.00640  -0.0367   0.8778   1.0000
   1.000   0.2807   0.01631   0.00639  -0.0383   0.8508   1.0000
   1.250   0.3151   0.01638   0.00639  -0.0389   0.8221   1.0000
   1.500   0.3459   0.01649   0.00642  -0.0387   0.7920   1.0000
   1.750   0.3741   0.01664   0.00648  -0.0380   0.7613   1.0000
   2.000   0.4006   0.01683   0.00657  -0.0371   0.7304   1.0000
   2.250   0.4262   0.01705   0.00671  -0.0360   0.6993   1.0000
   2.500   0.4512   0.01730   0.00686  -0.0348   0.6684   1.0000
   2.750   0.4759   0.01758   0.00704  -0.0337   0.6375   1.0000
   3.000   0.5004   0.01788   0.00727  -0.0325   0.6069   1.0000
   3.250   0.5247   0.01822   0.00752  -0.0314   0.5766   1.0000
   3.500   0.5490   0.01858   0.00779  -0.0304   0.5466   1.0000
   3.750   0.5732   0.01897   0.00811  -0.0294   0.5171   1.0000
   4.000   0.5978   0.01940   0.00850  -0.0285   0.4878   1.0000
   4.250   0.6223   0.01986   0.00891  -0.0277   0.4590   1.0000
   4.500   0.6468   0.02036   0.00936  -0.0269   0.4308   1.0000
   4.750   0.6711   0.02089   0.00988  -0.0262   0.4035   1.0000
   5.000   0.6952   0.02146   0.01040  -0.0254   0.3773   1.0000
   5.250   0.7192   0.02207   0.01099  -0.0247   0.3516   1.0000
   5.500   0.7431   0.02273   0.01167  -0.0240   0.3269   1.0000
   5.750   0.7666   0.02343   0.01238  -0.0233   0.3039   1.0000
   6.000   0.7901   0.02418   0.01318  -0.0226   0.2815   1.0000
   6.250   0.8131   0.02498   0.01396  -0.0219   0.2611   1.0000
   6.500   0.8362   0.02586   0.01493  -0.0213   0.2410   1.0000
   6.750   0.8586   0.02677   0.01588  -0.0205   0.2225   1.0000
   7.000   0.8808   0.02774   0.01691  -0.0198   0.2058   1.0000
   7.250   0.9026   0.02880   0.01804  -0.0191   0.1894   1.0000
   7.500   0.9240   0.02994   0.01931  -0.0183   0.1739   1.0000
   7.750   0.9447   0.03115   0.02065  -0.0175   0.1593   1.0000
   8.000   0.9650   0.03246   0.02210  -0.0167   0.1462   1.0000
   8.250   0.9843   0.03381   0.02355  -0.0159   0.1336   1.0000
   8.500   1.0030   0.03531   0.02519  -0.0150   0.1221   1.0000
   8.750   1.0200   0.03697   0.02710  -0.0141   0.1106   1.0000
   9.000   1.0361   0.03891   0.02929  -0.0131   0.1008   1.0000
   9.250   1.0509   0.04071   0.03119  -0.0122   0.0922   1.0000
   9.500   1.0642   0.04280   0.03356  -0.0111   0.0846   1.0000
   9.750   1.0747   0.04528   0.03632  -0.0101   0.0781   1.0000
  10.000   1.0839   0.04771   0.03900  -0.0090   0.0726   1.0000
  10.250   1.0919   0.05023   0.04162  -0.0081   0.0684   1.0000
  10.500   1.0890   0.05394   0.04583  -0.0070   0.0650   1.0000
  10.750   1.0854   0.05722   0.04939  -0.0060   0.0622   1.0000
  11.000   1.0799   0.06034   0.05267  -0.0050   0.0604   1.0000
  11.250   1.0736   0.06373   0.05619  -0.0046   0.0591   1.0000
  11.500   1.0663   0.06756   0.06008  -0.0049   0.0580   1.0000
  11.750   1.0450   0.07329   0.06605  -0.0074   0.0580   1.0000
  12.000   1.0213   0.08028   0.07323  -0.0116   0.0581   1.0000
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