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

S4062-095-87 (s4062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4062-095-87 (s4062-il)
Reynolds number: 1,000,000
Max Cl/Cd: 154.97 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4062-il-1000000.txt
Download as CSV file: xf-s4062-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2201   0.08436   0.08255  -0.0509   0.8897   0.0106
  -9.500  -0.2148   0.08113   0.07929  -0.0519   0.8850   0.0109
  -9.250  -0.2117   0.07726   0.07542  -0.0534   0.8800   0.0109
  -9.000  -0.2079   0.07372   0.07186  -0.0546   0.8750   0.0113
  -8.750  -0.2063   0.06982   0.06795  -0.0560   0.8701   0.0117
  -8.500  -0.2058   0.06565   0.06378  -0.0575   0.8648   0.0119
  -8.250  -0.2072   0.06126   0.05937  -0.0591   0.8595   0.0123
  -8.000  -0.2491   0.06896   0.06703  -0.0697   0.8770   0.0114
  -7.750  -0.2540   0.06566   0.06372  -0.0707   0.8678   0.0120
  -7.500  -0.2571   0.06144   0.05948  -0.0740   0.8591   0.0120
  -7.250  -0.3125   0.02826   0.02548  -0.0982   0.8445   0.0095
  -7.000  -0.3020   0.02187   0.01838  -0.0997   0.8391   0.0092
  -6.750  -0.2816   0.01855   0.01458  -0.0999   0.8343   0.0090
  -6.500  -0.2581   0.01648   0.01215  -0.0999   0.8301   0.0090
  -6.250  -0.2331   0.01482   0.01018  -0.0998   0.8261   0.0090
  -6.000  -0.2069   0.01362   0.00878  -0.0998   0.8218   0.0090
  -5.750  -0.1800   0.01287   0.00788  -0.0997   0.8176   0.0094
  -5.500  -0.1531   0.01214   0.00699  -0.0996   0.8137   0.0096
  -5.250  -0.1259   0.01133   0.00606  -0.0996   0.8098   0.0097
  -5.000  -0.0984   0.01066   0.00529  -0.0995   0.8055   0.0098
  -4.750  -0.0707   0.01021   0.00474  -0.0995   0.8015   0.0101
  -4.500  -0.0437   0.00932   0.00371  -0.0994   0.7976   0.0109
  -4.250  -0.0155   0.00896   0.00331  -0.0995   0.7935   0.0118
  -4.000   0.0128   0.00868   0.00298  -0.0996   0.7893   0.0127
  -3.750   0.0410   0.00846   0.00269  -0.0996   0.7854   0.0136
  -3.500   0.0693   0.00810   0.00229  -0.0996   0.7814   0.0163
  -3.250   0.0977   0.00778   0.00200  -0.0997   0.7772   0.0262
  -3.000   0.1258   0.00748   0.00179  -0.0998   0.7731   0.0537
  -2.750   0.1539   0.00732   0.00167  -0.0999   0.7691   0.0733
  -2.500   0.1825   0.00715   0.00156  -0.1001   0.7649   0.0937
  -2.250   0.2109   0.00699   0.00147  -0.1002   0.7606   0.1184
  -2.000   0.2391   0.00682   0.00138  -0.1003   0.7565   0.1528
  -1.750   0.2675   0.00667   0.00132  -0.1005   0.7523   0.1884
  -1.500   0.2959   0.00652   0.00127  -0.1006   0.7477   0.2236
  -1.250   0.3242   0.00638   0.00122  -0.1008   0.7432   0.2653
  -1.000   0.3525   0.00626   0.00118  -0.1009   0.7386   0.3106
  -0.750   0.3808   0.00608   0.00116  -0.1010   0.7332   0.3667
  -0.500   0.4087   0.00593   0.00114  -0.1011   0.7270   0.4273
  -0.250   0.4367   0.00573   0.00114  -0.1012   0.7202   0.5046
   0.000   0.4642   0.00553   0.00114  -0.1012   0.7131   0.5926
   0.250   0.4912   0.00527   0.00117  -0.1010   0.7061   0.7020
   0.500   0.5159   0.00497   0.00122  -0.1002   0.6993   0.8278
   0.750   0.5472   0.00469   0.00120  -0.1006   0.6932   0.9925
   1.000   0.5763   0.00473   0.00120  -0.1008   0.6863   1.0000
   1.250   0.6044   0.00479   0.00122  -0.1009   0.6795   1.0000
   1.500   0.6326   0.00484   0.00124  -0.1009   0.6720   1.0000
   1.750   0.6607   0.00491   0.00126  -0.1009   0.6648   1.0000
   2.000   0.6887   0.00497   0.00129  -0.1010   0.6566   1.0000
   2.250   0.7167   0.00504   0.00134  -0.1010   0.6482   1.0000
   2.750   0.7724   0.00521   0.00144  -0.1010   0.6285   1.0000
   3.000   0.8001   0.00530   0.00150  -0.1010   0.6170   1.0000
   3.250   0.8275   0.00542   0.00158  -0.1009   0.6038   1.0000
   3.500   0.8548   0.00554   0.00166  -0.1008   0.5890   1.0000
   3.750   0.8818   0.00569   0.00175  -0.1007   0.5714   1.0000
   4.000   0.9083   0.00589   0.00187  -0.1005   0.5508   1.0000
   4.250   0.9342   0.00613   0.00202  -0.1002   0.5237   1.0000
   4.500   0.9595   0.00643   0.00219  -0.0999   0.4905   1.0000
   4.750   0.9832   0.00686   0.00243  -0.0993   0.4449   1.0000
   5.000   1.0054   0.00745   0.00275  -0.0985   0.3895   1.0000
   5.250   1.0278   0.00800   0.00307  -0.0978   0.3409   1.0000
   5.500   1.0513   0.00844   0.00336  -0.0972   0.3083   1.0000
   5.750   1.0751   0.00884   0.00364  -0.0967   0.2807   1.0000
   6.000   1.0979   0.00930   0.00396  -0.0960   0.2496   1.0000
   6.250   1.1208   0.00975   0.00428  -0.0953   0.2219   1.0000
   6.500   1.1437   0.01018   0.00459  -0.0947   0.1981   1.0000
   6.750   1.1660   0.01064   0.00494  -0.0939   0.1745   1.0000
   7.000   1.1887   0.01105   0.00527  -0.0933   0.1559   1.0000
   7.250   1.2101   0.01154   0.00565  -0.0924   0.1350   1.0000
   7.500   1.2317   0.01200   0.00603  -0.0915   0.1168   1.0000
   7.750   1.2524   0.01251   0.00645  -0.0905   0.0993   1.0000
   8.000   1.2722   0.01305   0.00691  -0.0894   0.0823   1.0000
   8.250   1.2919   0.01358   0.00737  -0.0883   0.0681   1.0000
   8.500   1.3110   0.01412   0.00785  -0.0871   0.0559   1.0000
   8.750   1.3294   0.01468   0.00836  -0.0857   0.0457   1.0000
   9.000   1.3466   0.01528   0.00891  -0.0842   0.0362   1.0000
   9.250   1.3595   0.01600   0.00957  -0.0819   0.0248   1.0000
   9.500   1.3702   0.01678   0.01029  -0.0793   0.0175   1.0000
   9.750   1.3839   0.01741   0.01095  -0.0772   0.0151   1.0000
  10.000   1.3962   0.01815   0.01171  -0.0751   0.0133   1.0000
  10.250   1.4086   0.01894   0.01256  -0.0730   0.0123   1.0000
  10.500   1.4227   0.01963   0.01331  -0.0712   0.0118   1.0000
  10.750   1.4359   0.02039   0.01415  -0.0694   0.0113   1.0000
  11.000   1.4485   0.02123   0.01504  -0.0677   0.0107   1.0000
  11.250   1.4598   0.02216   0.01603  -0.0658   0.0102   1.0000
  11.500   1.4671   0.02344   0.01738  -0.0636   0.0094   1.0000
  11.750   1.4702   0.02506   0.01912  -0.0611   0.0091   1.0000
  12.000   1.4830   0.02598   0.02010  -0.0598   0.0088   1.0000
  12.250   1.4920   0.02721   0.02142  -0.0581   0.0087   1.0000
  12.500   1.5014   0.02845   0.02274  -0.0566   0.0084   1.0000
  12.750   1.5091   0.02986   0.02424  -0.0551   0.0082   1.0000
  13.000   1.5179   0.03121   0.02566  -0.0537   0.0078   1.0000
  13.250   1.5254   0.03271   0.02723  -0.0524   0.0075   1.0000
  13.500   1.5309   0.03441   0.02902  -0.0511   0.0073   1.0000
  13.750   1.5345   0.03636   0.03104  -0.0498   0.0070   1.0000
  14.000   1.5321   0.03896   0.03374  -0.0484   0.0068   1.0000
  14.250   1.5216   0.04251   0.03744  -0.0469   0.0065   1.0000
  14.500   1.5160   0.04573   0.04079  -0.0459   0.0064   1.0000
  14.750   1.5235   0.04761   0.04276  -0.0455   0.0063   1.0000
  15.000   1.5247   0.05030   0.04556  -0.0451   0.0062   1.0000
  15.250   1.5270   0.05295   0.04831  -0.0449   0.0060   1.0000
  15.500   1.5274   0.05593   0.05140  -0.0449   0.0059   1.0000
  15.750   1.5250   0.05939   0.05499  -0.0450   0.0058   1.0000
  16.000   1.5237   0.06287   0.05858  -0.0455   0.0056   1.0000
  16.250   1.5214   0.06658   0.06240  -0.0461   0.0055   1.0000
  16.500   1.5146   0.07111   0.06706  -0.0472   0.0054   1.0000
  16.750   1.5089   0.07565   0.07171  -0.0484   0.0053   1.0000
  17.000   1.5042   0.08023   0.07640  -0.0500   0.0052   1.0000
  17.250   1.4942   0.08583   0.08214  -0.0520   0.0051   1.0000
  17.500   1.4865   0.09124   0.08766  -0.0542   0.0050   1.0000
  17.750   1.4750   0.09751   0.09406  -0.0570   0.0050   1.0000
  18.000   1.4652   0.10369   0.10035  -0.0599   0.0049   1.0000
  18.250   1.4528   0.11048   0.10727  -0.0632   0.0049   1.0000
  18.500   1.4399   0.11756   0.11447  -0.0669   0.0048   1.0000
  18.750   1.4266   0.12482   0.12186  -0.0708   0.0048   1.0000
  19.000   1.4130   0.13228   0.12944  -0.0750   0.0047   1.0000
<< Back to S4062-095-87 (s4062-il)

Polar data table (+)

Polar graphs


<< Back to S4062-095-87 (s4062-il)