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SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SIKORSKY SSC-A07 AIRFOIL (ssca07-il)
Reynolds number: 200,000
Max Cl/Cd: 50.53 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ssca07-il-200000.txt
Download as CSV file: xf-ssca07-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SIKORSKY SSC-A07 AIRFOIL                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.6162   0.08776   0.08450  -0.0047   1.0000   0.0278
  -7.750  -0.6114   0.08301   0.07964  -0.0083   1.0000   0.0278
  -7.500  -0.6141   0.07528   0.07187  -0.0115   1.0000   0.0284
  -7.250  -0.6101   0.07018   0.06683  -0.0117   1.0000   0.0294
  -7.000  -0.6009   0.06648   0.06311  -0.0125   1.0000   0.0306
  -6.750  -0.5894   0.06247   0.05902  -0.0142   1.0000   0.0320
  -6.500  -0.5754   0.05833   0.05471  -0.0162   1.0000   0.0347
  -6.250  -0.5491   0.05661   0.05231  -0.0184   1.0000   0.0398
  -6.000  -0.5415   0.04866   0.04435  -0.0200   1.0000   0.0417
  -5.750  -0.5246   0.04545   0.04115  -0.0205   1.0000   0.0443
  -5.500  -0.5040   0.04231   0.03779  -0.0209   1.0000   0.0486
  -5.250  -0.4827   0.03867   0.03358  -0.0211   1.0000   0.0547
  -5.000  -0.4631   0.03570   0.03064  -0.0212   1.0000   0.0583
  -3.500  -0.3341   0.02084   0.01371  -0.0128   1.0000   0.0492
  -3.250  -0.3085   0.01914   0.01160  -0.0109   1.0000   0.0389
  -3.000  -0.2845   0.01715   0.00944  -0.0098   1.0000   0.0368
  -2.750  -0.2602   0.01581   0.00798  -0.0089   1.0000   0.0359
  -2.500  -0.2359   0.01472   0.00683  -0.0080   1.0000   0.0361
  -2.250  -0.2115   0.01384   0.00589  -0.0073   1.0000   0.0376
  -2.000  -0.1866   0.01303   0.00507  -0.0069   1.0000   0.0416
  -1.750  -0.1609   0.01235   0.00438  -0.0068   1.0000   0.0497
  -1.500  -0.1324   0.01142   0.00365  -0.0072   1.0000   0.1028
  -1.250  -0.1272   0.00865   0.00401  -0.0009   1.0000   0.9139
  -1.000  -0.0724   0.00874   0.00395  -0.0053   1.0000   1.0000
  -0.750  -0.0596   0.00875   0.00384  -0.0033   1.0000   1.0000
  -0.500  -0.0322   0.00882   0.00380  -0.0040   0.9982   1.0000
  -0.250   0.0188   0.00894   0.00380  -0.0090   0.9912   1.0000
   0.000   0.1108   0.00889   0.00365  -0.0215   0.9778   1.0000
   0.250   0.1657   0.00884   0.00356  -0.0268   0.9659   1.0000
   0.500   0.1999   0.00887   0.00357  -0.0280   0.9544   1.0000
   0.750   0.2257   0.00892   0.00360  -0.0274   0.9412   1.0000
   1.000   0.2469   0.00894   0.00362  -0.0257   0.9273   1.0000
   1.250   0.2661   0.00894   0.00361  -0.0235   0.9134   1.0000
   1.500   0.2845   0.00889   0.00358  -0.0211   0.8985   1.0000
   1.750   0.3032   0.00881   0.00349  -0.0186   0.8827   1.0000
   2.000   0.3227   0.00870   0.00339  -0.0163   0.8662   1.0000
   2.250   0.3429   0.00859   0.00327  -0.0140   0.8488   1.0000
   2.500   0.3649   0.00850   0.00318  -0.0122   0.8249   1.0000
   2.750   0.3867   0.00841   0.00309  -0.0102   0.7945   1.0000
   3.000   0.4095   0.00836   0.00299  -0.0086   0.7464   1.0000
   3.250   0.4305   0.00852   0.00279  -0.0063   0.6414   1.0000
   3.500   0.4516   0.00966   0.00291  -0.0050   0.4344   1.0000
   3.750   0.4764   0.01071   0.00333  -0.0051   0.3224   1.0000
   4.000   0.5026   0.01139   0.00378  -0.0052   0.2770   1.0000
   4.250   0.5291   0.01192   0.00417  -0.0053   0.2477   1.0000
   4.500   0.5557   0.01240   0.00458  -0.0054   0.2268   1.0000
   4.750   0.5822   0.01289   0.00500  -0.0054   0.2091   1.0000
   5.000   0.6091   0.01326   0.00544  -0.0054   0.1911   1.0000
   5.250   0.6358   0.01364   0.00583  -0.0055   0.1718   1.0000
   5.500   0.6626   0.01399   0.00621  -0.0056   0.1493   1.0000
   5.750   0.6892   0.01438   0.00658  -0.0057   0.1167   1.0000
   6.000   0.7146   0.01525   0.00720  -0.0056   0.0746   1.0000
   6.250   0.7393   0.01642   0.00840  -0.0052   0.0561   1.0000
   6.500   0.7629   0.01788   0.00990  -0.0047   0.0476   1.0000
   6.750   0.7869   0.01911   0.01114  -0.0043   0.0410   1.0000
   7.000   0.8103   0.02110   0.01327  -0.0036   0.0381   1.0000
   7.250   0.8350   0.02273   0.01513  -0.0030   0.0360   1.0000
   7.500   0.8591   0.02476   0.01744  -0.0024   0.0344   1.0000
   7.750   0.8820   0.02725   0.02034  -0.0017   0.0335   1.0000
   8.000   0.9035   0.02956   0.02297  -0.0010   0.0320   1.0000
   8.250   0.9225   0.03212   0.02572  -0.0006   0.0298   1.0000
   8.500   0.9371   0.03623   0.03034   0.0003   0.0294   1.0000
   8.750   0.9477   0.04073   0.03536   0.0013   0.0294   1.0000
   9.000   0.9495   0.04651   0.04165   0.0022   0.0290   1.0000
   9.250   0.9444   0.05265   0.04826   0.0029   0.0287   1.0000
   9.500   0.9367   0.05816   0.05414   0.0034   0.0286   1.0000
   9.750   0.9003   0.06976   0.06645   0.0022   0.0409   1.0000
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