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

S4233-136-84 (s4233-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4233-136-84 (s4233-il)
Reynolds number: 500,000
Max Cl/Cd: 104.55 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4233-il-500000-n5.txt
Download as CSV file: xf-s4233-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4233-136-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3933   0.09556   0.09328  -0.0476   0.9773   0.0095
 -11.250  -0.5110   0.05562   0.05307  -0.0759   0.9499   0.0086
 -11.000  -0.5546   0.04372   0.04069  -0.0876   0.9127   0.0084
 -10.750  -0.5685   0.04030   0.03705  -0.0888   0.8918   0.0084
 -10.500  -0.5905   0.03698   0.03345  -0.0878   0.8731   0.0084
 -10.250  -0.5970   0.03538   0.03166  -0.0855   0.8603   0.0085
 -10.000  -0.6027   0.03267   0.02864  -0.0838   0.8495   0.0085
  -9.750  -0.5993   0.03040   0.02607  -0.0824   0.8399   0.0086
  -9.500  -0.5917   0.02814   0.02350  -0.0811   0.8317   0.0086
  -9.250  -0.5795   0.02624   0.02132  -0.0801   0.8239   0.0087
  -9.000  -0.5642   0.02453   0.01934  -0.0792   0.8169   0.0088
  -8.750  -0.5465   0.02304   0.01760  -0.0784   0.8096   0.0089
  -8.500  -0.5269   0.02174   0.01607  -0.0777   0.8031   0.0090
  -8.250  -0.5059   0.02057   0.01471  -0.0772   0.7963   0.0092
  -8.000  -0.4841   0.01953   0.01346  -0.0766   0.7901   0.0093
  -7.750  -0.4611   0.01859   0.01237  -0.0761   0.7834   0.0095
  -7.500  -0.4377   0.01777   0.01139  -0.0757   0.7771   0.0097
  -7.250  -0.4135   0.01703   0.01053  -0.0753   0.7711   0.0099
  -7.000  -0.3890   0.01639   0.00977  -0.0750   0.7646   0.0101
  -6.750  -0.3640   0.01584   0.00909  -0.0747   0.7588   0.0102
  -6.500  -0.3402   0.01498   0.00817  -0.0743   0.7525   0.0104
  -6.250  -0.3161   0.01428   0.00739  -0.0740   0.7464   0.0107
  -6.000  -0.2908   0.01374   0.00679  -0.0738   0.7405   0.0110
  -5.750  -0.2649   0.01329   0.00629  -0.0736   0.7344   0.0114
  -5.500  -0.2388   0.01292   0.00584  -0.0735   0.7288   0.0120
  -5.250  -0.2123   0.01253   0.00540  -0.0734   0.7227   0.0125
  -5.000  -0.1857   0.01216   0.00495  -0.0733   0.7167   0.0129
  -4.750  -0.1589   0.01184   0.00455  -0.0732   0.7113   0.0133
  -4.500  -0.1318   0.01152   0.00418  -0.0732   0.7052   0.0137
  -4.250  -0.1048   0.01121   0.00379  -0.0731   0.6996   0.0145
  -4.000  -0.0773   0.01097   0.00350  -0.0731   0.6940   0.0154
  -3.750  -0.0497   0.01076   0.00323  -0.0731   0.6880   0.0167
  -3.500  -0.0222   0.01057   0.00299  -0.0731   0.6827   0.0194
  -3.250   0.0049   0.01020   0.00273  -0.0731   0.6769   0.0428
  -3.000   0.0314   0.00977   0.00249  -0.0732   0.6711   0.0983
  -2.750   0.0582   0.00940   0.00231  -0.0732   0.6658   0.1552
  -2.500   0.0852   0.00905   0.00216  -0.0734   0.6599   0.2176
  -2.250   0.1122   0.00874   0.00204  -0.0734   0.6544   0.2826
  -2.000   0.1386   0.00832   0.00194  -0.0735   0.6490   0.3791
  -1.750   0.1656   0.00805   0.00189  -0.0736   0.6432   0.4508
  -1.500   0.1930   0.00792   0.00185  -0.0736   0.6377   0.4983
  -1.250   0.2210   0.00783   0.00184  -0.0736   0.6321   0.5323
  -1.000   0.2490   0.00778   0.00182  -0.0737   0.6263   0.5597
  -0.750   0.2770   0.00776   0.00181  -0.0737   0.6209   0.5828
  -0.500   0.3051   0.00773   0.00182  -0.0738   0.6150   0.6038
  -0.250   0.3332   0.00773   0.00182  -0.0738   0.6091   0.6225
   0.000   0.3613   0.00774   0.00183  -0.0739   0.6036   0.6388
   0.250   0.3895   0.00774   0.00185  -0.0740   0.5975   0.6535
   0.750   0.4455   0.00778   0.00190  -0.0741   0.5856   0.6818
   1.000   0.4734   0.00781   0.00193  -0.0741   0.5794   0.6963
   1.250   0.5012   0.00784   0.00198  -0.0742   0.5734   0.7107
   1.750   0.5565   0.00791   0.00208  -0.0741   0.5604   0.7387
   2.000   0.5842   0.00793   0.00215  -0.0741   0.5536   0.7527
   2.250   0.6113   0.00798   0.00222  -0.0740   0.5467   0.7674
   2.500   0.6387   0.00801   0.00229  -0.0740   0.5396   0.7827
   2.750   0.6654   0.00807   0.00238  -0.0738   0.5323   0.7992
   3.000   0.6922   0.00811   0.00247  -0.0736   0.5248   0.8170
   3.250   0.7182   0.00817   0.00257  -0.0732   0.5170   0.8365
   3.500   0.7440   0.00820   0.00268  -0.0728   0.5091   0.8584
   4.000   0.7939   0.00830   0.00290  -0.0716   0.4926   0.9149
   4.250   0.8243   0.00839   0.00302  -0.0721   0.4837   0.9507
   4.500   0.8619   0.00851   0.00314  -0.0745   0.4731   0.9915
   4.750   0.8894   0.00867   0.00328  -0.0746   0.4631   1.0000
   5.000   0.9151   0.00886   0.00343  -0.0744   0.4527   1.0000
   5.250   0.9405   0.00906   0.00361  -0.0741   0.4414   1.0000
   5.500   0.9661   0.00925   0.00379  -0.0739   0.4294   1.0000
   5.750   0.9911   0.00948   0.00399  -0.0736   0.4165   1.0000
   6.000   1.0155   0.00974   0.00422  -0.0732   0.4016   1.0000
   6.250   1.0390   0.01004   0.00446  -0.0726   0.3844   1.0000
   6.750   1.0843   0.01074   0.00504  -0.0713   0.3461   1.0000
   7.000   1.1035   0.01127   0.00542  -0.0702   0.3150   1.0000
   7.250   1.1202   0.01193   0.00589  -0.0687   0.2783   1.0000
   7.500   1.1377   0.01253   0.00635  -0.0673   0.2497   1.0000
   7.750   1.1547   0.01312   0.00683  -0.0658   0.2237   1.0000
   8.000   1.1678   0.01388   0.00743  -0.0638   0.1918   1.0000
   8.250   1.1777   0.01467   0.00805  -0.0613   0.1613   1.0000
   8.500   1.1855   0.01547   0.00872  -0.0584   0.1360   1.0000
   8.750   1.1922   0.01638   0.00949  -0.0555   0.1107   1.0000
   9.000   1.1993   0.01733   0.01033  -0.0529   0.0889   1.0000
   9.250   1.2065   0.01834   0.01125  -0.0505   0.0709   1.0000
   9.500   1.2151   0.01932   0.01218  -0.0484   0.0567   1.0000
   9.750   1.2232   0.02039   0.01319  -0.0464   0.0444   1.0000
  10.000   1.2321   0.02146   0.01424  -0.0447   0.0355   1.0000
  10.250   1.2389   0.02273   0.01547  -0.0428   0.0260   1.0000
  10.500   1.2459   0.02403   0.01676  -0.0411   0.0180   1.0000
  10.750   1.2527   0.02542   0.01815  -0.0395   0.0133   1.0000
  11.000   1.2609   0.02675   0.01951  -0.0382   0.0112   1.0000
  11.250   1.2694   0.02811   0.02092  -0.0370   0.0101   1.0000
  11.500   1.2784   0.02946   0.02234  -0.0359   0.0094   1.0000
  11.750   1.2868   0.03090   0.02384  -0.0349   0.0090   1.0000
  12.000   1.2937   0.03251   0.02552  -0.0339   0.0085   1.0000
  12.250   1.3004   0.03419   0.02727  -0.0329   0.0082   1.0000
  12.500   1.3046   0.03613   0.02929  -0.0320   0.0078   1.0000
  12.750   1.3108   0.03795   0.03120  -0.0313   0.0077   1.0000
  13.000   1.3163   0.03989   0.03322  -0.0306   0.0076   1.0000
  13.250   1.3206   0.04200   0.03542  -0.0300   0.0073   1.0000
  13.500   1.3248   0.04419   0.03770  -0.0296   0.0071   1.0000
  13.750   1.3283   0.04653   0.04012  -0.0293   0.0071   1.0000
  14.000   1.3306   0.04906   0.04275  -0.0290   0.0069   1.0000
  14.250   1.3324   0.05171   0.04550  -0.0289   0.0067   1.0000
  14.500   1.3333   0.05457   0.04845  -0.0289   0.0066   1.0000
  14.750   1.3342   0.05752   0.05149  -0.0291   0.0065   1.0000
  15.000   1.3335   0.06070   0.05478  -0.0294   0.0064   1.0000
  15.250   1.3335   0.06392   0.05808  -0.0298   0.0063   1.0000
  15.500   1.3309   0.06756   0.06182  -0.0304   0.0062   1.0000
  15.750   1.3281   0.07132   0.06568  -0.0311   0.0061   1.0000
  16.000   1.3246   0.07527   0.06972  -0.0320   0.0060   1.0000
  16.250   1.3190   0.07962   0.07417  -0.0332   0.0058   1.0000
  16.500   1.3135   0.08406   0.07871  -0.0344   0.0058   1.0000
<< Back to S4233-136-84 (s4233-il)

Polar data table (+)

Polar graphs


<< Back to S4233-136-84 (s4233-il)