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S4062-095-87 (s4062-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4062-095-87 (s4062-il)
Reynolds number: 200,000
Max Cl/Cd: 86.3 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4062-il-200000-n5.txt
Download as CSV file: xf-s4062-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4062-095-87                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2682   0.08608   0.08262  -0.0585   0.9658   0.0163
  -8.500  -0.2562   0.08139   0.07792  -0.0634   0.9575   0.0156
  -8.000  -0.2577   0.06687   0.06341  -0.0757   0.9315   0.0133
  -7.750  -0.2569   0.06300   0.05954  -0.0790   0.9195   0.0132
  -7.500  -0.2556   0.05745   0.05396  -0.0848   0.9084   0.0130
  -7.250  -0.2522   0.05038   0.04679  -0.0920   0.8988   0.0128
  -7.000  -0.2528   0.03895   0.03494  -0.1004   0.8888   0.0125
  -6.750  -0.2450   0.03165   0.02695  -0.1040   0.8811   0.0123
  -6.500  -0.2290   0.02708   0.02170  -0.1050   0.8752   0.0123
  -6.250  -0.2084   0.02399   0.01800  -0.1052   0.8705   0.0125
  -6.000  -0.1852   0.02178   0.01531  -0.1051   0.8650   0.0128
  -5.750  -0.1607   0.02013   0.01325  -0.1048   0.8606   0.0131
  -5.500  -0.1360   0.01874   0.01161  -0.1045   0.8568   0.0136
  -5.250  -0.1103   0.01800   0.01079  -0.1045   0.8516   0.0150
  -5.000  -0.0842   0.01720   0.00983  -0.1043   0.8472   0.0164
  -4.750  -0.0581   0.01634   0.00878  -0.1040   0.8435   0.0174
  -4.500  -0.0319   0.01550   0.00782  -0.1038   0.8388   0.0186
  -4.250  -0.0053   0.01490   0.00713  -0.1037   0.8341   0.0204
  -4.000   0.0217   0.01434   0.00644  -0.1034   0.8303   0.0232
  -3.750   0.0487   0.01382   0.00588  -0.1033   0.8264   0.0305
  -3.500   0.0756   0.01332   0.00541  -0.1032   0.8214   0.0465
  -3.250   0.1028   0.01294   0.00508  -0.1031   0.8172   0.0699
  -3.000   0.1300   0.01263   0.00483  -0.1031   0.8138   0.1018
  -2.750   0.1572   0.01238   0.00463  -0.1031   0.8089   0.1283
  -2.500   0.1846   0.01215   0.00445  -0.1030   0.8044   0.1561
  -2.250   0.2120   0.01193   0.00425  -0.1030   0.8006   0.1871
  -2.000   0.2394   0.01172   0.00412  -0.1029   0.7965   0.2232
  -1.750   0.2666   0.01154   0.00402  -0.1029   0.7915   0.2652
  -1.500   0.2938   0.01132   0.00392  -0.1028   0.7873   0.3146
  -1.250   0.3211   0.01109   0.00382  -0.1027   0.7839   0.3745
  -1.000   0.3475   0.01087   0.00383  -0.1026   0.7785   0.4483
  -0.750   0.3735   0.01060   0.00381  -0.1022   0.7739   0.5355
  -0.500   0.3985   0.01028   0.00379  -0.1014   0.7702   0.6397
  -0.250   0.4204   0.00996   0.00385  -0.0998   0.7650   0.7650
   0.000   0.4557   0.00961   0.00376  -0.1006   0.7604   0.9552
   0.250   0.4874   0.00962   0.00366  -0.1013   0.7562   1.0000
   0.500   0.5147   0.00970   0.00367  -0.1012   0.7507   1.0000
   0.750   0.5420   0.00976   0.00366  -0.1011   0.7448   1.0000
   1.000   0.5696   0.00980   0.00361  -0.1009   0.7397   1.0000
   1.250   0.5964   0.00987   0.00364  -0.1007   0.7313   1.0000
   1.500   0.6237   0.00989   0.00359  -0.1004   0.7237   1.0000
   1.750   0.6505   0.00994   0.00359  -0.1001   0.7144   1.0000
   2.000   0.6774   0.00999   0.00361  -0.0998   0.7052   1.0000
   2.250   0.7047   0.01004   0.00360  -0.0996   0.6970   1.0000
   2.500   0.7313   0.01012   0.00369  -0.0993   0.6873   1.0000
   2.750   0.7583   0.01020   0.00374  -0.0991   0.6782   1.0000
   3.000   0.7851   0.01028   0.00379  -0.0988   0.6686   1.0000
   3.250   0.8116   0.01037   0.00391  -0.0985   0.6574   1.0000
   3.500   0.8380   0.01047   0.00400  -0.0981   0.6458   1.0000
   3.750   0.8644   0.01058   0.00411  -0.0978   0.6333   1.0000
   4.000   0.8904   0.01071   0.00424  -0.0974   0.6188   1.0000
   4.250   0.9161   0.01085   0.00436  -0.0969   0.6024   1.0000
   4.500   0.9414   0.01101   0.00449  -0.0964   0.5831   1.0000
   4.750   0.9660   0.01121   0.00465  -0.0957   0.5597   1.0000
   5.000   0.9899   0.01147   0.00485  -0.0949   0.5316   1.0000
   5.250   1.0124   0.01182   0.00508  -0.0940   0.4971   1.0000
   5.500   1.0332   0.01229   0.00537  -0.0928   0.4562   1.0000
   5.750   1.0523   0.01288   0.00578  -0.0914   0.4130   1.0000
   6.000   1.0705   0.01354   0.00625  -0.0899   0.3721   1.0000
   6.250   1.0882   0.01424   0.00677  -0.0884   0.3352   1.0000
   6.500   1.1060   0.01493   0.00732  -0.0870   0.3014   1.0000
   6.750   1.1235   0.01563   0.00788  -0.0856   0.2708   1.0000
   7.000   1.1410   0.01631   0.00848  -0.0842   0.2443   1.0000
   7.250   1.1587   0.01697   0.00907  -0.0828   0.2216   1.0000
   7.500   1.1762   0.01761   0.00967  -0.0814   0.2029   1.0000
   7.750   1.1936   0.01825   0.01029  -0.0799   0.1845   1.0000
   8.000   1.2091   0.01897   0.01096  -0.0783   0.1651   1.0000
   8.250   1.2227   0.01971   0.01166  -0.0763   0.1461   1.0000
   8.500   1.2352   0.02052   0.01240  -0.0743   0.1262   1.0000
   8.750   1.2466   0.02144   0.01322  -0.0722   0.1059   1.0000
   9.000   1.2586   0.02235   0.01408  -0.0703   0.0892   1.0000
   9.250   1.2709   0.02329   0.01500  -0.0685   0.0762   1.0000
   9.500   1.2827   0.02429   0.01599  -0.0667   0.0646   1.0000
   9.750   1.2941   0.02535   0.01706  -0.0650   0.0545   1.0000
  10.000   1.3048   0.02648   0.01821  -0.0632   0.0461   1.0000
  10.250   1.3143   0.02775   0.01947  -0.0615   0.0390   1.0000
  10.500   1.3246   0.02897   0.02079  -0.0598   0.0332   1.0000
  10.750   1.3326   0.03044   0.02230  -0.0581   0.0287   1.0000
  11.000   1.3409   0.03188   0.02385  -0.0564   0.0254   1.0000
  11.250   1.3462   0.03363   0.02563  -0.0547   0.0229   1.0000
  11.500   1.3540   0.03519   0.02735  -0.0533   0.0210   1.0000
  11.750   1.3606   0.03689   0.02918  -0.0519   0.0196   1.0000
  12.000   1.3653   0.03881   0.03119  -0.0505   0.0185   1.0000
  12.250   1.3665   0.04111   0.03359  -0.0492   0.0176   1.0000
  12.500   1.3690   0.04337   0.03599  -0.0479   0.0171   1.0000
  12.750   1.3718   0.04567   0.03845  -0.0469   0.0166   1.0000
  13.000   1.3734   0.04816   0.04109  -0.0460   0.0161   1.0000
  13.250   1.3748   0.05075   0.04383  -0.0452   0.0156   1.0000
  13.500   1.3754   0.05349   0.04671  -0.0446   0.0151   1.0000
  13.750   1.3759   0.05632   0.04968  -0.0442   0.0146   1.0000
  14.000   1.3755   0.05937   0.05288  -0.0440   0.0140   1.0000
  14.250   1.3733   0.06275   0.05638  -0.0441   0.0137   1.0000
  14.500   1.3694   0.06647   0.06022  -0.0443   0.0133   1.0000
  14.750   1.3641   0.07053   0.06439  -0.0447   0.0130   1.0000
  15.000   1.3616   0.07440   0.06845  -0.0452   0.0127   1.0000
  15.250   1.3581   0.07852   0.07277  -0.0460   0.0125   1.0000
  15.500   1.3537   0.08292   0.07736  -0.0471   0.0124   1.0000
  15.750   1.3480   0.08768   0.08232  -0.0485   0.0121   1.0000
  16.000   1.3413   0.09276   0.08760  -0.0502   0.0119   1.0000
  16.250   1.3336   0.09818   0.09321  -0.0524   0.0118   1.0000
  16.500   1.3248   0.10400   0.09922  -0.0549   0.0115   1.0000
  16.750   1.3153   0.11017   0.10559  -0.0579   0.0114   1.0000
  17.000   1.3052   0.11666   0.11226  -0.0613   0.0112   1.0000
  17.250   1.2943   0.12352   0.11931  -0.0651   0.0111   1.0000
  17.500   1.2828   0.13073   0.12669  -0.0693   0.0109   1.0000
  17.750   1.2702   0.13845   0.13460  -0.0740   0.0109   1.0000
  18.000   1.2570   0.14660   0.14292  -0.0791   0.0108   1.0000
  18.250   1.2420   0.15558   0.15207  -0.0848   0.0108   1.0000
  18.500   1.2236   0.16590   0.16258  -0.0916   0.0109   1.0000
  18.750   1.1969   0.17956   0.17644  -0.1005   0.0112   1.0000
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