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S2048 (s2048-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S2048 (s2048-il)
Reynolds number: 100,000
Max Cl/Cd: 55.79 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2048-il-100000.txt
Download as CSV file: xf-s2048-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4536   0.09232   0.08745  -0.0295   1.0000   0.1041
  -8.250  -0.4716   0.08955   0.08481  -0.0325   1.0000   0.1074
  -8.000  -0.4977   0.08645   0.08186  -0.0373   1.0000   0.1082
  -7.750  -0.4925   0.08218   0.07765  -0.0348   1.0000   0.1106
  -7.500  -0.4805   0.07980   0.07528  -0.0307   1.0000   0.1154
  -7.250  -0.4913   0.07605   0.07159  -0.0339   1.0000   0.1196
  -7.000  -0.5183   0.07160   0.06700  -0.0405   1.0000   0.1234
  -6.750  -0.4992   0.06877   0.06435  -0.0349   1.0000   0.1277
  -6.500  -0.5167   0.06533   0.06059  -0.0400   1.0000   0.1371
  -6.250  -0.5017   0.06180   0.05732  -0.0355   1.0000   0.1412
  -6.000  -0.5028   0.05827   0.05361  -0.0370   1.0000   0.1526
  -5.750  -0.4930   0.05567   0.05107  -0.0348   1.0000   0.1603
  -5.500  -0.4897   0.05253   0.04769  -0.0358   1.0000   0.1801
  -5.250  -0.4801   0.04988   0.04510  -0.0337   1.0000   0.1956
  -5.000  -0.4407   0.03823   0.03159  -0.0399   1.0000   0.0940
  -4.750  -0.4181   0.03290   0.02579  -0.0394   1.0000   0.0772
  -4.500  -0.3917   0.03006   0.02193  -0.0380   1.0000   0.0678
  -4.250  -0.3685   0.02694   0.01847  -0.0375   1.0000   0.0667
  -4.000  -0.3442   0.02484   0.01600  -0.0367   1.0000   0.0667
  -3.750  -0.3203   0.02290   0.01388  -0.0362   1.0000   0.0709
  -3.500  -0.2961   0.02160   0.01245  -0.0354   1.0000   0.0745
  -3.250  -0.2717   0.02038   0.01109  -0.0345   1.0000   0.0777
  -3.000  -0.2479   0.01920   0.00985  -0.0336   1.0000   0.0828
  -2.750  -0.2249   0.01831   0.00897  -0.0327   1.0000   0.0948
  -2.500  -0.2017   0.01707   0.00802  -0.0322   1.0000   0.1284
  -2.250  -0.1833   0.01414   0.00759  -0.0307   1.0000   0.6186
  -2.000  -0.1760   0.01403   0.00794  -0.0252   1.0000   0.7716
  -1.750  -0.1699   0.01396   0.00804  -0.0196   1.0000   0.8551
  -1.500  -0.1409   0.01381   0.00788  -0.0189   1.0000   0.9534
  -1.250  -0.1097   0.01376   0.00758  -0.0210   1.0000   1.0000
  -1.000  -0.0852   0.01392   0.00749  -0.0216   1.0000   1.0000
  -0.750  -0.0611   0.01413   0.00749  -0.0221   1.0000   1.0000
  -0.500  -0.0376   0.01438   0.00754  -0.0223   1.0000   1.0000
  -0.250  -0.0145   0.01467   0.00767  -0.0224   1.0000   1.0000
   0.000   0.0079   0.01500   0.00786  -0.0224   1.0000   1.0000
   0.250   0.0495   0.01562   0.00834  -0.0261   0.9933   1.0000
   0.500   0.0960   0.01625   0.00885  -0.0306   0.9840   1.0000
   0.750   0.1404   0.01675   0.00926  -0.0345   0.9732   1.0000
   1.000   0.1853   0.01719   0.00965  -0.0384   0.9616   1.0000
   1.250   0.2316   0.01752   0.00995  -0.0424   0.9491   1.0000
   1.500   0.2783   0.01774   0.01016  -0.0462   0.9361   1.0000
   1.750   0.3246   0.01782   0.01028  -0.0497   0.9229   1.0000
   2.000   0.3705   0.01780   0.01030  -0.0530   0.9101   1.0000
   2.250   0.4166   0.01767   0.01024  -0.0561   0.8975   1.0000
   2.500   0.4667   0.01737   0.01007  -0.0597   0.8861   1.0000
   2.750   0.5155   0.01694   0.00976  -0.0629   0.8739   1.0000
   3.000   0.5586   0.01645   0.00940  -0.0647   0.8602   1.0000
   3.250   0.5986   0.01592   0.00905  -0.0658   0.8445   1.0000
   3.500   0.6327   0.01546   0.00873  -0.0657   0.8246   1.0000
   3.750   0.6719   0.01483   0.00822  -0.0662   0.8041   1.0000
   4.000   0.7035   0.01438   0.00788  -0.0653   0.7757   1.0000
   4.250   0.7303   0.01407   0.00767  -0.0636   0.7366   1.0000
   4.500   0.7558   0.01387   0.00742  -0.0616   0.6818   1.0000
   4.750   0.7783   0.01395   0.00725  -0.0592   0.6057   1.0000
   5.000   0.7976   0.01450   0.00736  -0.0568   0.5191   1.0000
   5.250   0.8159   0.01534   0.00778  -0.0547   0.4479   1.0000
   5.500   0.8346   0.01621   0.00838  -0.0530   0.3916   1.0000
   5.750   0.8534   0.01707   0.00902  -0.0514   0.3430   1.0000
   6.000   0.8717   0.01795   0.00971  -0.0498   0.2957   1.0000
   6.250   0.8882   0.01896   0.01047  -0.0480   0.2418   1.0000
   6.500   0.9032   0.02034   0.01154  -0.0460   0.1802   1.0000
   6.750   0.9196   0.02179   0.01275  -0.0442   0.1375   1.0000
   7.000   0.9385   0.02342   0.01423  -0.0426   0.1136   1.0000
   7.250   0.9583   0.02499   0.01571  -0.0414   0.0954   1.0000
   7.500   0.9804   0.02696   0.01764  -0.0404   0.0820   1.0000
   7.750   1.0027   0.02904   0.01983  -0.0395   0.0702   1.0000
   8.000   1.0242   0.03137   0.02234  -0.0384   0.0604   1.0000
   8.250   1.0482   0.03525   0.02622  -0.0381   0.0545   1.0000
   8.500   1.0642   0.03722   0.02885  -0.0359   0.0500   1.0000
   8.750   1.0809   0.03972   0.03160  -0.0344   0.0460   1.0000
   9.000   1.0948   0.04326   0.03546  -0.0328   0.0444   1.0000
   9.250   1.1039   0.04747   0.04008  -0.0308   0.0438   1.0000
   9.500   1.1079   0.05161   0.04471  -0.0282   0.0439   1.0000
   9.750   1.1026   0.05579   0.04952  -0.0248   0.0450   1.0000
  10.000   1.0780   0.06124   0.05568  -0.0206   0.0471   1.0000
  10.250   1.0567   0.06579   0.06058  -0.0175   0.0485   1.0000
  10.500   1.0341   0.07007   0.06508  -0.0152   0.0495   1.0000
  10.750   1.0107   0.07476   0.06996  -0.0144   0.0503   1.0000
  11.000   0.9864   0.08011   0.07546  -0.0155   0.0510   1.0000
  11.250   0.9628   0.08634   0.08179  -0.0184   0.0517   1.0000
  11.500   0.9423   0.09346   0.08899  -0.0225   0.0526   1.0000
  11.750   0.9322   0.10026   0.09579  -0.0255   0.0538   1.0000
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