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

SM701 (sm701-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SM701 (sm701-il)
Reynolds number: 100,000
Max Cl/Cd: 50.76 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sm701-il-100000.txt
Download as CSV file: xf-sm701-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4308   0.10625   0.10207  -0.0279   1.0000   0.1498
  -8.500  -0.4469   0.10402   0.09991  -0.0269   1.0000   0.1542
  -8.250  -0.5330   0.10014   0.09622  -0.0305   1.0000   0.1582
  -8.000  -0.5064   0.09751   0.09360  -0.0265   1.0000   0.1614
  -7.750  -0.4784   0.09551   0.09157  -0.0259   0.9972   0.1679
  -7.250  -0.4900   0.08747   0.08360  -0.0318   0.9866   0.1836
  -6.750  -0.5878   0.05339   0.04724  -0.0562   0.9705   0.0818
  -6.500  -0.5731   0.04970   0.04329  -0.0563   0.9658   0.0795
  -6.250  -0.5497   0.04587   0.03895  -0.0576   0.9617   0.0768
  -6.000  -0.5169   0.04229   0.03428  -0.0594   0.9584   0.0720
  -5.750  -0.4920   0.04066   0.03229  -0.0595   0.9540   0.0714
  -5.500  -0.4658   0.03870   0.03005  -0.0598   0.9497   0.0714
  -5.250  -0.4340   0.03668   0.02782  -0.0610   0.9461   0.0721
  -5.000  -0.3995   0.03528   0.02641  -0.0628   0.9428   0.0750
  -4.750  -0.3805   0.03440   0.02549  -0.0617   0.9374   0.0776
  -4.500  -0.3503   0.03352   0.02450  -0.0622   0.9330   0.0804
  -4.250  -0.3127   0.03285   0.02368  -0.0638   0.9294   0.0836
  -4.000  -0.2944   0.03185   0.02286  -0.0626   0.9239   0.0876
  -3.750  -0.2658   0.03133   0.02237  -0.0630   0.9189   0.0960
  -3.500  -0.2280   0.03056   0.02177  -0.0652   0.9151   0.1132
  -3.250  -0.2039   0.02898   0.02077  -0.0659   0.9095   0.1788
  -3.000  -0.1784   0.02799   0.02180  -0.0658   0.9044   0.5943
  -2.750  -0.1480   0.02938   0.02317  -0.0643   0.8996   0.6447
  -2.500  -0.1429   0.03025   0.02407  -0.0590   0.8911   0.6743
  -2.250  -0.1215   0.03147   0.02529  -0.0553   0.8854   0.7066
  -2.000  -0.1128   0.03206   0.02586  -0.0510   0.8772   0.7241
  -1.750  -0.0888   0.03260   0.02633  -0.0488   0.8709   0.7416
  -1.500  -0.0753   0.03303   0.02671  -0.0455   0.8628   0.7579
  -1.250  -0.0608   0.03347   0.02714  -0.0410   0.8555   0.7775
  -1.000  -0.0515   0.03379   0.02744  -0.0364   0.8471   0.7959
  -0.750  -0.0279   0.03385   0.02741  -0.0349   0.8396   0.8104
  -0.500  -0.0012   0.03383   0.02729  -0.0351   0.8312   0.8176
  -0.250   0.0362   0.03368   0.02700  -0.0374   0.8234   0.8236
   0.000   0.0616   0.03360   0.02686  -0.0371   0.8145   0.8286
   0.250   0.0992   0.03338   0.02654  -0.0391   0.8068   0.8338
   0.500   0.1314   0.03335   0.02641  -0.0407   0.7976   0.8391
   0.750   0.1674   0.03299   0.02599  -0.0418   0.7901   0.8432
   1.000   0.1936   0.03293   0.02588  -0.0419   0.7800   0.8484
   1.250   0.2386   0.03249   0.02536  -0.0449   0.7734   0.8536
   1.500   0.2630   0.03239   0.02524  -0.0446   0.7626   0.8581
   1.750   0.3068   0.03168   0.02449  -0.0465   0.7567   0.8629
   2.000   0.3339   0.03158   0.02436  -0.0468   0.7455   0.8691
   2.250   0.3791   0.03065   0.02340  -0.0487   0.7403   0.8738
   2.500   0.4267   0.02954   0.02226  -0.0508   0.7363   0.8786
   2.750   0.4536   0.02922   0.02194  -0.0507   0.7245   0.8855
   3.000   0.5063   0.02769   0.02040  -0.0531   0.7221   0.8908
   3.250   0.5274   0.02744   0.02017  -0.0519   0.7090   0.8986
   3.500   0.5873   0.02582   0.01853  -0.0558   0.7060   0.9037
   3.750   0.6084   0.02541   0.01815  -0.0542   0.6929   0.9121
   4.000   0.6756   0.02378   0.01650  -0.0594   0.6889   0.9180
   4.250   0.6971   0.02325   0.01600  -0.0578   0.6748   0.9283
   4.500   0.7277   0.02257   0.01535  -0.0577   0.6612   0.9384
   4.750   0.7664   0.02179   0.01457  -0.0590   0.6473   0.9485
   5.000   0.8077   0.02106   0.01385  -0.0608   0.6312   0.9598
   5.250   0.8528   0.02043   0.01320  -0.0636   0.6122   0.9718
   5.750   0.9361   0.01970   0.01234  -0.0689   0.5650   1.0000
   6.000   0.9681   0.01961   0.01207  -0.0700   0.5418   1.0000
   6.250   0.9946   0.01987   0.01220  -0.0705   0.5164   1.0000
   6.500   1.0278   0.02025   0.01235  -0.0721   0.4924   1.0000
   6.750   1.0555   0.02082   0.01279  -0.0729   0.4689   1.0000
   7.000   1.0863   0.02144   0.01324  -0.0743   0.4478   1.0000
   7.250   1.1173   0.02215   0.01375  -0.0756   0.4285   1.0000
   7.500   1.1436   0.02290   0.01441  -0.0761   0.4106   1.0000
   7.750   1.1704   0.02368   0.01509  -0.0767   0.3942   1.0000
   8.000   1.1982   0.02447   0.01576  -0.0774   0.3793   1.0000
   8.250   1.2210   0.02526   0.01652  -0.0772   0.3653   1.0000
   8.500   1.2427   0.02608   0.01736  -0.0769   0.3524   1.0000
   8.750   1.2667   0.02696   0.01821  -0.0768   0.3408   1.0000
   9.000   1.2957   0.02783   0.01895  -0.0776   0.3297   1.0000
   9.250   1.3125   0.02867   0.01988  -0.0764   0.3192   1.0000
   9.500   1.3351   0.02962   0.02085  -0.0761   0.3097   1.0000
   9.750   1.3605   0.03050   0.02167  -0.0763   0.3003   1.0000
  10.000   1.3754   0.03150   0.02280  -0.0748   0.2918   1.0000
  10.250   1.4063   0.03244   0.02362  -0.0759   0.2830   1.0000
  10.500   1.4142   0.03349   0.02490  -0.0733   0.2757   1.0000
  10.750   1.4425   0.03442   0.02575  -0.0739   0.2677   1.0000
  11.000   1.4510   0.03559   0.02711  -0.0715   0.2610   1.0000
  11.250   1.4696   0.03657   0.02814  -0.0707   0.2540   1.0000
  11.500   1.4890   0.03782   0.02945  -0.0701   0.2474   1.0000
  11.750   1.4946   0.03901   0.03083  -0.0674   0.2413   1.0000
  12.000   1.5296   0.04010   0.03178  -0.0691   0.2341   1.0000
  12.250   1.5225   0.04154   0.03354  -0.0648   0.2293   1.0000
  12.500   1.5341   0.04271   0.03482  -0.0631   0.2235   1.0000
  12.750   1.5574   0.04403   0.03613  -0.0632   0.2175   1.0000
  13.000   1.5487   0.04574   0.03814  -0.0592   0.2129   1.0000
  13.250   1.5600   0.04696   0.03943  -0.0578   0.2076   1.0000
  13.500   1.5789   0.04845   0.04094  -0.0574   0.2021   1.0000
  13.750   1.5639   0.05063   0.04344  -0.0534   0.1983   1.0000
  14.000   1.5654   0.05230   0.04526  -0.0513   0.1936   1.0000
  14.250   1.5941   0.05338   0.04625  -0.0519   0.1878   1.0000
  14.500   1.5685   0.05641   0.04964  -0.0478   0.1850   1.0000
  14.750   1.5529   0.05929   0.05279  -0.0451   0.1814   1.0000
  15.000   1.5833   0.05959   0.05296  -0.0455   0.1755   1.0000
  15.250   1.5703   0.06283   0.05643  -0.0434   0.1723   1.0000
  15.500   1.5341   0.06766   0.06162  -0.0409   0.1703   1.0000
  15.750   1.4977   0.07320   0.06748  -0.0394   0.1683   1.0000
  16.000   1.4605   0.07953   0.07408  -0.0390   0.1663   1.0000
  16.250   1.4318   0.08551   0.08026  -0.0395   0.1638   1.0000
  16.500   1.3882   0.09407   0.08903  -0.0415   0.1622   1.0000
  16.750   1.3420   0.10419   0.09932  -0.0449   0.1605   1.0000
  17.000   0.9839   0.20310   0.19808  -0.0978   0.2040   1.0000
<< Back to SM701 (sm701-il)

Polar data table (+)

Polar graphs


<< Back to SM701 (sm701-il)