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S2048 (s2048-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S2048 (s2048-il)
Reynolds number: 200,000
Max Cl/Cd: 67.53 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2048-il-200000-n5.txt
Download as CSV file: xf-s2048-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2048                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4690   0.08813   0.08455  -0.0325   1.0000   0.0141
  -9.000  -0.4744   0.08359   0.08006  -0.0342   1.0000   0.0139
  -8.750  -0.4835   0.07848   0.07502  -0.0363   1.0000   0.0134
  -8.500  -0.4957   0.07356   0.07018  -0.0383   1.0000   0.0134
  -8.250  -0.5286   0.06425   0.06095  -0.0444   1.0000   0.0125
  -8.000  -0.5455   0.05771   0.05432  -0.0463   1.0000   0.0123
  -7.750  -0.5569   0.05187   0.04831  -0.0464   1.0000   0.0121
  -7.500  -0.5650   0.04698   0.04324  -0.0457   1.0000   0.0122
  -7.250  -0.5679   0.04241   0.03836  -0.0447   1.0000   0.0123
  -7.000  -0.5635   0.03847   0.03411  -0.0440   0.9997   0.0126
  -6.750  -0.5378   0.03520   0.03051  -0.0467   0.9962   0.0133
  -6.500  -0.5100   0.03290   0.02792  -0.0489   0.9931   0.0148
  -6.250  -0.4837   0.02907   0.02353  -0.0504   0.9892   0.0162
  -6.000  -0.4552   0.02545   0.01930  -0.0516   0.9859   0.0169
  -5.750  -0.4241   0.02298   0.01632  -0.0529   0.9835   0.0176
  -5.500  -0.3942   0.02161   0.01459  -0.0535   0.9802   0.0184
  -5.250  -0.3668   0.01949   0.01226  -0.0542   0.9765   0.0206
  -5.000  -0.3358   0.01826   0.01082  -0.0551   0.9735   0.0215
  -4.750  -0.3035   0.01713   0.00955  -0.0562   0.9711   0.0226
  -4.500  -0.2724   0.01619   0.00850  -0.0571   0.9680   0.0238
  -4.250  -0.2444   0.01543   0.00763  -0.0573   0.9632   0.0250
  -4.000  -0.2123   0.01487   0.00698  -0.0583   0.9598   0.0269
  -3.750  -0.1791   0.01412   0.00615  -0.0597   0.9572   0.0296
  -3.500  -0.1491   0.01363   0.00559  -0.0603   0.9528   0.0318
  -3.250  -0.1189   0.01322   0.00510  -0.0608   0.9481   0.0359
  -3.000  -0.0853   0.01277   0.00466  -0.0621   0.9449   0.0508
  -2.750  -0.0508   0.01226   0.00431  -0.0638   0.9426   0.0957
  -2.500  -0.0247   0.01178   0.00405  -0.0638   0.9359   0.1592
  -2.250   0.0045   0.01080   0.00381  -0.0649   0.9318   0.3479
  -2.000   0.0337   0.00998   0.00384  -0.0654   0.9287   0.5681
  -1.750   0.0582   0.00981   0.00384  -0.0645   0.9212   0.6360
  -1.500   0.0892   0.00967   0.00375  -0.0649   0.9169   0.6782
  -1.250   0.1162   0.00954   0.00373  -0.0644   0.9107   0.7212
  -1.000   0.1441   0.00941   0.00368  -0.0640   0.9045   0.7605
  -0.750   0.1722   0.00928   0.00361  -0.0637   0.8976   0.7873
  -0.500   0.2018   0.00914   0.00347  -0.0636   0.8896   0.8056
  -0.250   0.2298   0.00901   0.00334  -0.0633   0.8791   0.8219
   0.000   0.2589   0.00886   0.00318  -0.0631   0.8671   0.8384
   0.250   0.2878   0.00872   0.00304  -0.0628   0.8536   0.8559
   0.500   0.3165   0.00861   0.00292  -0.0625   0.8399   0.8748
   0.750   0.3453   0.00853   0.00283  -0.0622   0.8264   0.8962
   1.000   0.3762   0.00847   0.00277  -0.0625   0.8128   0.9200
   1.250   0.4111   0.00843   0.00273  -0.0638   0.7987   0.9462
   1.500   0.4490   0.00841   0.00268  -0.0658   0.7834   0.9763
   1.750   0.4817   0.00844   0.00266  -0.0668   0.7663   1.0000
   2.000   0.5079   0.00852   0.00270  -0.0664   0.7477   1.0000
   2.250   0.5338   0.00862   0.00274  -0.0659   0.7262   1.0000
   2.500   0.5595   0.00874   0.00279  -0.0654   0.7017   1.0000
   2.750   0.5848   0.00889   0.00286  -0.0647   0.6721   1.0000
   3.000   0.6094   0.00909   0.00296  -0.0639   0.6351   1.0000
   3.250   0.6328   0.00937   0.00306  -0.0629   0.5879   1.0000
   3.500   0.6548   0.00976   0.00321  -0.0617   0.5311   1.0000
   3.750   0.6751   0.01030   0.00343  -0.0603   0.4650   1.0000
   4.000   0.6951   0.01092   0.00372  -0.0589   0.3997   1.0000
   4.250   0.7163   0.01150   0.00408  -0.0578   0.3465   1.0000
   4.500   0.7385   0.01202   0.00442  -0.0570   0.3052   1.0000
   4.750   0.7617   0.01248   0.00477  -0.0563   0.2722   1.0000
   5.000   0.7849   0.01294   0.00513  -0.0556   0.2425   1.0000
   5.250   0.8082   0.01341   0.00551  -0.0550   0.2137   1.0000
   5.500   0.8313   0.01390   0.00592  -0.0543   0.1848   1.0000
   5.750   0.8540   0.01445   0.00640  -0.0536   0.1518   1.0000
   6.000   0.8762   0.01508   0.00689  -0.0529   0.1170   1.0000
   6.250   0.8974   0.01583   0.00749  -0.0520   0.0872   1.0000
   6.500   0.9192   0.01655   0.00815  -0.0512   0.0682   1.0000
   6.750   0.9411   0.01724   0.00887  -0.0503   0.0571   1.0000
   7.000   0.9623   0.01801   0.00965  -0.0493   0.0486   1.0000
   7.250   0.9836   0.01875   0.01046  -0.0484   0.0402   1.0000
   7.500   1.0057   0.01936   0.01114  -0.0477   0.0322   1.0000
   7.750   1.0261   0.02016   0.01197  -0.0467   0.0260   1.0000
   8.000   1.0465   0.02096   0.01287  -0.0456   0.0212   1.0000
   8.250   1.0639   0.02215   0.01416  -0.0441   0.0173   1.0000
   8.500   1.0824   0.02315   0.01528  -0.0428   0.0145   1.0000
   8.750   1.0982   0.02444   0.01663  -0.0413   0.0124   1.0000
   9.000   1.1160   0.02547   0.01783  -0.0400   0.0107   1.0000
   9.250   1.1314   0.02675   0.01931  -0.0383   0.0098   1.0000
   9.500   1.1458   0.02807   0.02077  -0.0367   0.0091   1.0000
   9.750   1.1576   0.02963   0.02248  -0.0347   0.0086   1.0000
  10.000   1.1647   0.03173   0.02476  -0.0323   0.0082   1.0000
  10.250   1.1721   0.03366   0.02691  -0.0298   0.0079   1.0000
  10.500   1.1780   0.03569   0.02920  -0.0273   0.0077   1.0000
  10.750   1.1811   0.03797   0.03174  -0.0246   0.0076   1.0000
  11.000   1.1813   0.04040   0.03445  -0.0220   0.0075   1.0000
  11.250   1.1780   0.04315   0.03749  -0.0194   0.0073   1.0000
  11.500   1.1714   0.04620   0.04083  -0.0172   0.0073   1.0000
  11.750   1.1623   0.04953   0.04444  -0.0154   0.0072   1.0000
  12.000   1.1499   0.05340   0.04859  -0.0144   0.0072   1.0000
  12.250   1.1343   0.05796   0.05341  -0.0144   0.0071   1.0000
  12.500   1.1182   0.06299   0.05868  -0.0154   0.0071   1.0000
  12.750   1.1007   0.06883   0.06475  -0.0178   0.0072   1.0000
  13.000   1.0825   0.07558   0.07170  -0.0216   0.0072   1.0000
  13.250   1.0614   0.08398   0.08031  -0.0271   0.0072   1.0000
  13.500   1.0407   0.09345   0.08995  -0.0337   0.0073   1.0000
  13.750   1.0208   0.10358   0.10022  -0.0404   0.0074   1.0000
  14.000   0.9972   0.11527   0.11201  -0.0477   0.0076   1.0000
  14.250   0.9708   0.12833   0.12514  -0.0553   0.0078   1.0000
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