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SM701 (sm701-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SM701 (sm701-il)
Reynolds number: 50,000
Max Cl/Cd: 26.97 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sm701-il-50000.txt
Download as CSV file: xf-sm701-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SM701                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3494   0.11241   0.10638  -0.0110   1.0000   0.3692
  -7.750  -0.3580   0.11051   0.10457  -0.0088   1.0000   0.3776
  -6.750  -0.6366   0.07391   0.06787  -0.0339   1.0000   0.1570
  -6.500  -0.6442   0.06685   0.06025  -0.0363   1.0000   0.1413
  -6.250  -0.6355   0.06278   0.05606  -0.0360   1.0000   0.1371
  -6.000  -0.6277   0.05752   0.05019  -0.0376   1.0000   0.1311
  -5.750  -0.6114   0.05366   0.04536  -0.0390   1.0000   0.1266
  -5.500  -0.5931   0.05059   0.04196  -0.0392   1.0000   0.1262
  -5.250  -0.5730   0.04777   0.03881  -0.0392   1.0000   0.1256
  -5.000  -0.5515   0.04526   0.03594  -0.0392   1.0000   0.1252
  -4.750  -0.5291   0.04313   0.03344  -0.0390   1.0000   0.1254
  -4.500  -0.5057   0.04142   0.03128  -0.0387   1.0000   0.1270
  -4.250  -0.4853   0.03963   0.02954  -0.0381   1.0000   0.1312
  -4.000  -0.4641   0.03846   0.02828  -0.0374   1.0000   0.1369
  -3.750  -0.4418   0.03745   0.02699  -0.0364   1.0000   0.1422
  -3.500  -0.4227   0.03637   0.02608  -0.0347   1.0000   0.1489
  -3.250  -0.4028   0.03565   0.02533  -0.0331   1.0000   0.1600
  -3.000  -0.3839   0.03480   0.02468  -0.0317   1.0000   0.1787
  -2.750  -0.3621   0.03342   0.02371  -0.0312   1.0000   0.2233
  -2.500  -0.3577   0.03258   0.02571  -0.0240   1.0000   0.6377
  -2.250  -0.3684   0.03433   0.02753  -0.0128   1.0000   0.7009
  -2.000  -0.3775   0.03547   0.02867  -0.0026   1.0000   0.7457
  -1.750  -0.3850   0.03615   0.02932   0.0066   1.0000   0.7841
  -1.500  -0.3896   0.03647   0.02957   0.0145   1.0000   0.8177
  -1.250  -0.3913   0.03659   0.02959   0.0214   1.0000   0.8491
  -1.000  -0.3896   0.03661   0.02951   0.0273   1.0000   0.8813
  -0.750  -0.2084   0.04185   0.03398   0.0051   1.0000   0.9736
  -0.500  -0.1610   0.04247   0.03436  -0.0014   1.0000   0.9850
  -0.250  -0.1233   0.04302   0.03473  -0.0063   1.0000   0.9945
   0.000  -0.1030   0.04335   0.03493  -0.0083   1.0000   1.0000
   0.250  -0.1045   0.04312   0.03466  -0.0062   1.0000   1.0000
   0.500  -0.1065   0.04288   0.03438  -0.0041   1.0000   1.0000
   0.750   0.0159   0.04592   0.03707  -0.0237   0.9473   1.0000
   1.000   0.0535   0.04668   0.03770  -0.0278   0.9279   1.0000
   1.250   0.0723   0.04684   0.03779  -0.0286   0.9100   1.0000
   1.500   0.0918   0.04709   0.03797  -0.0293   0.8924   1.0000
   1.750   0.1106   0.04734   0.03816  -0.0299   0.8751   1.0000
   2.000   0.1292   0.04758   0.03833  -0.0302   0.8577   1.0000
   2.250   0.1469   0.04780   0.03850  -0.0303   0.8406   1.0000
   2.500   0.1671   0.04807   0.03871  -0.0307   0.8233   1.0000
   2.750   0.1958   0.04852   0.03908  -0.0324   0.8057   1.0000
   3.000   0.2310   0.04908   0.03957  -0.0349   0.7883   1.0000
   3.250   0.2693   0.04965   0.04009  -0.0378   0.7710   1.0000
   3.500   0.3040   0.05022   0.04060  -0.0402   0.7531   1.0000
   3.750   0.3337   0.05086   0.04122  -0.0420   0.7348   1.0000
   4.000   0.3668   0.05150   0.04184  -0.0441   0.7169   1.0000
   4.250   0.4013   0.05211   0.04243  -0.0462   0.6991   1.0000
   4.500   0.4366   0.05268   0.04299  -0.0483   0.6819   1.0000
   4.750   0.4719   0.05317   0.04348  -0.0502   0.6649   1.0000
   5.000   0.5069   0.05365   0.04395  -0.0519   0.6485   1.0000
   5.250   0.5420   0.05400   0.04431  -0.0534   0.6320   1.0000
   5.500   0.5762   0.05433   0.04465  -0.0546   0.6162   1.0000
   6.000   0.6479   0.05444   0.04480  -0.0566   0.5863   1.0000
   6.250   0.7068   0.05244   0.04285  -0.0582   0.5759   1.0000
   6.500   0.7354   0.05264   0.04308  -0.0583   0.5607   1.0000
   6.750   0.7616   0.05305   0.04351  -0.0582   0.5459   1.0000
   7.000   0.7865   0.05355   0.04406  -0.0580   0.5314   1.0000
   7.250   0.9028   0.04566   0.03623  -0.0610   0.5276   1.0000
   7.500   0.9363   0.04543   0.03605  -0.0611   0.5127   1.0000
   7.750   0.9710   0.04523   0.03588  -0.0613   0.4980   1.0000
   8.000   1.0054   0.04522   0.03592  -0.0616   0.4835   1.0000
   8.250   1.0444   0.04506   0.03579  -0.0624   0.4691   1.0000
   8.500   1.0846   0.04503   0.03577  -0.0634   0.4548   1.0000
   8.750   1.1280   0.04508   0.03584  -0.0649   0.4408   1.0000
   9.000   1.1748   0.04524   0.03598  -0.0670   0.4265   1.0000
   9.250   1.2256   0.04544   0.03613  -0.0696   0.4125   1.0000
   9.500   1.1487   0.05144   0.04241  -0.0599   0.4074   1.0000
   9.750   1.2094   0.05079   0.04176  -0.0628   0.3942   1.0000
  10.000   0.4960   0.12411   0.11607  -0.0583   0.5265   1.0000
  10.250   0.4910   0.12541   0.11742  -0.0581   0.5144   1.0000
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