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S4233-136-84 (s4233-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4233-136-84 (s4233-il)
Reynolds number: 100,000
Max Cl/Cd: 54.29 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4233-il-100000-n5.txt
Download as CSV file: xf-s4233-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3685   0.09129   0.08646  -0.0540   1.0000   0.0267
 -10.250  -0.3717   0.08687   0.08210  -0.0559   1.0000   0.0264
 -10.000  -0.3825   0.08079   0.07610  -0.0589   1.0000   0.0263
  -9.750  -0.3980   0.07441   0.06980  -0.0620   1.0000   0.0260
  -9.500  -0.4201   0.07005   0.06555  -0.0628   1.0000   0.0251
  -9.250  -0.4382   0.05915   0.05440  -0.0776   0.9785   0.0250
  -9.000  -0.4462   0.05272   0.04763  -0.0851   0.9612   0.0244
  -8.750  -0.4461   0.04796   0.04245  -0.0886   0.9476   0.0249
  -8.500  -0.4411   0.04409   0.03816  -0.0900   0.9355   0.0250
  -8.250  -0.4319   0.04071   0.03431  -0.0906   0.9252   0.0254
  -8.000  -0.4191   0.03767   0.03080  -0.0906   0.9160   0.0257
  -7.750  -0.4054   0.03516   0.02787  -0.0899   0.9061   0.0258
  -7.500  -0.3855   0.03278   0.02507  -0.0896   0.8993   0.0259
  -7.250  -0.3677   0.03088   0.02282  -0.0886   0.8899   0.0262
  -7.000  -0.3440   0.02906   0.02065  -0.0883   0.8840   0.0265
  -6.750  -0.3233   0.02763   0.01896  -0.0873   0.8753   0.0270
  -6.500  -0.2994   0.02621   0.01740  -0.0868   0.8694   0.0276
  -6.250  -0.2783   0.02512   0.01625  -0.0860   0.8612   0.0283
  -6.000  -0.2550   0.02417   0.01520  -0.0854   0.8549   0.0297
  -5.750  -0.2327   0.02338   0.01430  -0.0847   0.8476   0.0320
  -5.500  -0.2099   0.02256   0.01335  -0.0839   0.8409   0.0339
  -5.250  -0.1877   0.02172   0.01245  -0.0831   0.8346   0.0360
  -5.000  -0.1654   0.02104   0.01167  -0.0823   0.8272   0.0388
  -4.750  -0.1412   0.02029   0.01077  -0.0816   0.8221   0.0430
  -4.500  -0.1190   0.01966   0.01011  -0.0809   0.8142   0.0522
  -4.250  -0.0964   0.01868   0.00937  -0.0802   0.8084   0.0928
  -4.000  -0.0745   0.01784   0.00889  -0.0797   0.8019   0.1756
  -3.750  -0.0542   0.01692   0.00863  -0.0790   0.7952   0.3102
  -3.500  -0.0319   0.01630   0.00850  -0.0780   0.7906   0.4315
  -3.250  -0.0097   0.01615   0.00852  -0.0769   0.7828   0.4972
  -3.000   0.0157   0.01602   0.00838  -0.0761   0.7774   0.5433
  -2.750   0.0406   0.01598   0.00831  -0.0753   0.7713   0.5810
  -2.500   0.0655   0.01595   0.00825  -0.0745   0.7648   0.6137
  -2.250   0.0920   0.01588   0.00809  -0.0737   0.7602   0.6430
  -2.000   0.1159   0.01592   0.00812  -0.0728   0.7529   0.6682
  -1.750   0.1418   0.01589   0.00801  -0.0721   0.7473   0.6929
  -1.500   0.1675   0.01586   0.00793  -0.0713   0.7419   0.7139
  -1.250   0.1922   0.01588   0.00792  -0.0705   0.7350   0.7344
  -1.000   0.2186   0.01583   0.00777  -0.0699   0.7301   0.7547
  -0.750   0.2428   0.01587   0.00780  -0.0690   0.7233   0.7737
  -0.500   0.2681   0.01585   0.00774  -0.0682   0.7174   0.7926
  -0.250   0.2943   0.01581   0.00764  -0.0675   0.7125   0.8118
   0.000   0.3181   0.01587   0.00770  -0.0666   0.7052   0.8316
   0.250   0.3449   0.01581   0.00760  -0.0660   0.7000   0.8514
   0.500   0.3709   0.01585   0.00763  -0.0655   0.6934   0.8715
   0.750   0.3997   0.01585   0.00761  -0.0655   0.6872   0.8929
   1.000   0.4333   0.01579   0.00749  -0.0663   0.6823   0.9142
   1.250   0.4684   0.01588   0.00759  -0.0680   0.6745   0.9364
   1.500   0.5084   0.01584   0.00749  -0.0704   0.6691   0.9577
   1.750   0.5492   0.01592   0.00755  -0.0734   0.6618   0.9804
   2.000   0.5863   0.01595   0.00753  -0.0756   0.6554   1.0000
   2.250   0.6073   0.01609   0.00761  -0.0747   0.6487   1.0000
   2.500   0.6297   0.01624   0.00772  -0.0741   0.6416   1.0000
   2.750   0.6552   0.01633   0.00776  -0.0737   0.6357   1.0000
   3.000   0.6780   0.01656   0.00798  -0.0731   0.6277   1.0000
   3.250   0.7053   0.01661   0.00797  -0.0730   0.6220   1.0000
   3.500   0.7277   0.01689   0.00828  -0.0724   0.6133   1.0000
   3.750   0.7551   0.01696   0.00832  -0.0722   0.6072   1.0000
   4.000   0.7779   0.01724   0.00865  -0.0717   0.5985   1.0000
   4.250   0.8053   0.01732   0.00870  -0.0715   0.5920   1.0000
   4.500   0.8281   0.01761   0.00907  -0.0709   0.5830   1.0000
   4.750   0.8556   0.01770   0.00913  -0.0708   0.5763   1.0000
   5.000   0.8779   0.01800   0.00953  -0.0701   0.5667   1.0000
   5.250   0.9039   0.01816   0.00971  -0.0698   0.5590   1.0000
   5.500   0.9275   0.01841   0.01003  -0.0692   0.5497   1.0000
   5.750   0.9516   0.01865   0.01033  -0.0687   0.5408   1.0000
   6.000   0.9769   0.01882   0.01053  -0.0683   0.5320   1.0000
   6.250   0.9990   0.01913   0.01096  -0.0675   0.5216   1.0000
   6.500   1.0229   0.01937   0.01125  -0.0669   0.5119   1.0000
   6.750   1.0470   0.01958   0.01151  -0.0663   0.5016   1.0000
   7.000   1.0680   0.01991   0.01196  -0.0653   0.4897   1.0000
   7.250   1.0895   0.02021   0.01235  -0.0644   0.4777   1.0000
   7.500   1.1106   0.02051   0.01272  -0.0634   0.4650   1.0000
   7.750   1.1309   0.02083   0.01310  -0.0622   0.4513   1.0000
   8.000   1.1495   0.02119   0.01354  -0.0609   0.4361   1.0000
   8.250   1.1667   0.02160   0.01400  -0.0593   0.4199   1.0000
   8.500   1.1825   0.02206   0.01452  -0.0576   0.4031   1.0000
   8.750   1.1969   0.02258   0.01507  -0.0557   0.3858   1.0000
   9.000   1.2089   0.02317   0.01568  -0.0536   0.3677   1.0000
   9.250   1.2167   0.02386   0.01640  -0.0508   0.3487   1.0000
   9.500   1.2225   0.02470   0.01725  -0.0480   0.3281   1.0000
   9.750   1.2271   0.02568   0.01820  -0.0453   0.3073   1.0000
  10.000   1.2311   0.02684   0.01935  -0.0429   0.2852   1.0000
  10.250   1.2324   0.02822   0.02068  -0.0404   0.2623   1.0000
  10.500   1.2313   0.02989   0.02226  -0.0380   0.2361   1.0000
  10.750   1.2275   0.03189   0.02414  -0.0358   0.2079   1.0000
  11.000   1.2217   0.03424   0.02634  -0.0338   0.1789   1.0000
  11.250   1.2153   0.03682   0.02876  -0.0321   0.1513   1.0000
  11.500   1.2090   0.03958   0.03137  -0.0307   0.1261   1.0000
  11.750   1.2044   0.04235   0.03404  -0.0297   0.1063   1.0000
  12.000   1.2009   0.04514   0.03679  -0.0288   0.0900   1.0000
  12.250   1.1977   0.04802   0.03966  -0.0281   0.0769   1.0000
  12.500   1.1936   0.05110   0.04274  -0.0276   0.0651   1.0000
  12.750   1.1896   0.05432   0.04597  -0.0273   0.0554   1.0000
  13.000   1.1848   0.05775   0.04944  -0.0272   0.0482   1.0000
  13.250   1.1788   0.06146   0.05318  -0.0273   0.0427   1.0000
  13.500   1.1750   0.06505   0.05688  -0.0275   0.0387   1.0000
  13.750   1.1699   0.06892   0.06085  -0.0279   0.0356   1.0000
  14.000   1.1637   0.07305   0.06504  -0.0285   0.0332   1.0000
  14.250   1.1609   0.07683   0.06897  -0.0292   0.0306   1.0000
  14.500   1.1570   0.08086   0.07309  -0.0300   0.0287   1.0000
  14.750   1.1523   0.08507   0.07739  -0.0311   0.0275   1.0000
  15.000   1.1503   0.08895   0.08138  -0.0320   0.0260   1.0000
  15.250   1.1499   0.09264   0.08522  -0.0328   0.0249   1.0000
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