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SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il)
Reynolds number: 100,000
Max Cl/Cd: 33.67 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc1094r8-il-100000.txt
Download as CSV file: xf-sc1094r8-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SIKORSKY SC1094 R8 AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5039   0.11233   0.10727   0.0077   1.0000   0.0867
  -9.000  -0.4978   0.10893   0.10390   0.0067   1.0000   0.0893
  -8.750  -0.5048   0.10528   0.10030   0.0016   1.0000   0.0920
  -8.500  -0.5052   0.10105   0.09613  -0.0012   1.0000   0.0932
  -8.250  -0.4901   0.09780   0.09289   0.0007   1.0000   0.0956
  -8.000  -0.4886   0.09421   0.08935  -0.0018   1.0000   0.0988
  -7.750  -0.5148   0.08869   0.08383  -0.0164   1.0000   0.1011
  -7.500  -0.4919   0.08564   0.08089  -0.0097   1.0000   0.1030
  -7.250  -0.4832   0.08226   0.07753  -0.0106   1.0000   0.1064
  -7.000  -0.4919   0.07673   0.07184  -0.0206   1.0000   0.1110
  -6.750  -0.4745   0.07377   0.06902  -0.0173   1.0000   0.1136
  -6.500  -0.4755   0.06961   0.06457  -0.0241   1.0000   0.1212
  -6.250  -0.4577   0.06643   0.06160  -0.0208   1.0000   0.1244
  -6.000  -0.4511   0.06273   0.05770  -0.0240   1.0000   0.1334
  -5.750  -0.4358   0.05998   0.05507  -0.0223   1.0000   0.1385
  -5.500  -0.4260   0.05660   0.05156  -0.0233   1.0000   0.1475
  -5.250  -0.4153   0.05401   0.04877  -0.0239   1.0000   0.1592
  -5.000  -0.4013   0.05120   0.04612  -0.0220   1.0000   0.1645
  -4.750  -0.3901   0.04855   0.04339  -0.0214   1.0000   0.1767
  -4.500  -0.3781   0.04619   0.04095  -0.0205   1.0000   0.1913
  -4.250  -0.3659   0.04396   0.03870  -0.0192   1.0000   0.2075
  -4.000  -0.3536   0.04181   0.03658  -0.0176   1.0000   0.2255
  -3.750  -0.3411   0.03982   0.03464  -0.0157   1.0000   0.2462
  -3.000  -0.2400   0.02761   0.01951  -0.0164   1.0000   0.0918
  -2.750  -0.2169   0.02572   0.01746  -0.0155   1.0000   0.0886
  -2.500  -0.1913   0.02413   0.01532  -0.0143   1.0000   0.0844
  -2.250  -0.1670   0.02284   0.01389  -0.0135   1.0000   0.0840
  -2.000  -0.1426   0.02177   0.01269  -0.0129   1.0000   0.0855
  -1.750  -0.1187   0.02097   0.01196  -0.0124   1.0000   0.0892
  -1.500  -0.0933   0.02025   0.01113  -0.0119   1.0000   0.0919
  -1.250  -0.0684   0.01950   0.01049  -0.0117   1.0000   0.0956
  -1.000  -0.0210   0.01865   0.00981  -0.0155   0.9919   0.1066
  -0.750   0.0322   0.01767   0.00908  -0.0203   0.9798   0.1261
  -0.500   0.0843   0.01385   0.00848  -0.0218   0.9749   1.0000
  -0.250   0.1641   0.01371   0.00791  -0.0309   0.9563   1.0000
   0.000   0.2226   0.01345   0.00748  -0.0358   0.9323   1.0000
   0.250   0.2660   0.01316   0.00709  -0.0376   0.9057   1.0000
   0.500   0.2961   0.01291   0.00674  -0.0366   0.8745   1.0000
   0.750   0.3202   0.01269   0.00639  -0.0344   0.8400   1.0000
   1.000   0.3412   0.01255   0.00610  -0.0316   0.7993   1.0000
   1.250   0.3618   0.01247   0.00583  -0.0289   0.7511   1.0000
   1.500   0.3825   0.01251   0.00559  -0.0263   0.6937   1.0000
   1.750   0.4036   0.01273   0.00541  -0.0239   0.6273   1.0000
   2.000   0.4251   0.01313   0.00537  -0.0220   0.5563   1.0000
   2.250   0.4471   0.01369   0.00544  -0.0205   0.4914   1.0000
   2.500   0.4697   0.01432   0.00564  -0.0193   0.4338   1.0000
   2.750   0.4928   0.01500   0.00593  -0.0184   0.3839   1.0000
   3.000   0.5165   0.01572   0.00630  -0.0176   0.3431   1.0000
   3.250   0.5406   0.01646   0.00669  -0.0169   0.3125   1.0000
   3.500   0.5657   0.01711   0.00718  -0.0163   0.2873   1.0000
   3.750   0.5910   0.01778   0.00768  -0.0158   0.2681   1.0000
   4.000   0.6165   0.01848   0.00820  -0.0154   0.2528   1.0000
   4.250   0.6422   0.01917   0.00872  -0.0150   0.2402   1.0000
   4.500   0.6683   0.01985   0.00940  -0.0146   0.2288   1.0000
   4.750   0.6942   0.02070   0.01008  -0.0143   0.2200   1.0000
   5.000   0.7204   0.02141   0.01085  -0.0139   0.2116   1.0000
   5.250   0.7466   0.02237   0.01160  -0.0137   0.2051   1.0000
   5.500   0.7726   0.02320   0.01261  -0.0133   0.1986   1.0000
   5.750   0.7986   0.02404   0.01343  -0.0130   0.1928   1.0000
   6.000   0.8248   0.02533   0.01455  -0.0129   0.1883   1.0000
   6.250   0.8499   0.02633   0.01583  -0.0125   0.1843   1.0000
   6.500   0.8750   0.02740   0.01705  -0.0121   0.1800   1.0000
   6.750   0.9001   0.02845   0.01812  -0.0119   0.1761   1.0000
   7.000   0.9252   0.03007   0.01965  -0.0118   0.1730   1.0000
   7.250   0.9476   0.03157   0.02152  -0.0112   0.1707   1.0000
   7.500   0.9692   0.03327   0.02357  -0.0106   0.1682   1.0000
   7.750   0.9904   0.03499   0.02555  -0.0101   0.1655   1.0000
   8.000   1.0120   0.03662   0.02733  -0.0096   0.1630   1.0000
   8.250   1.0344   0.03824   0.02901  -0.0093   0.1610   1.0000
   8.500   1.0548   0.04038   0.03128  -0.0089   0.1595   1.0000
   8.750   1.0728   0.04335   0.03439  -0.0086   0.1583   1.0000
   9.000   1.0828   0.04644   0.03796  -0.0075   0.1575   1.0000
   9.250   1.0881   0.05015   0.04215  -0.0066   0.1567   1.0000
   9.500   1.0887   0.05450   0.04692  -0.0057   0.1563   1.0000
   9.750   1.0852   0.05945   0.05222  -0.0051   0.1567   1.0000
  10.000   1.0823   0.06451   0.05751  -0.0048   0.1574   1.0000
  10.250   1.0851   0.06930   0.06243  -0.0048   0.1581   1.0000
  10.500   0.7938   0.12492   0.11864  -0.0441   0.2235   1.0000
  10.750   0.8310   0.12832   0.12210  -0.0408   0.2219   1.0000
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