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S7012 8.75% (s7012-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 200,000
Max Cl/Cd: 70.3 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7012-il-200000.txt
Download as CSV file: xf-s7012-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7012 8.75%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4748   0.09265   0.08921  -0.0253   1.0000   0.0431
  -8.500  -0.4769   0.08832   0.08493  -0.0292   1.0000   0.0432
  -8.250  -0.4833   0.08327   0.07992  -0.0347   1.0000   0.0433
  -8.000  -0.4816   0.07864   0.07537  -0.0296   1.0000   0.0447
  -7.750  -0.4760   0.07620   0.07295  -0.0283   1.0000   0.0458
  -7.500  -0.4737   0.07254   0.06932  -0.0305   1.0000   0.0468
  -7.250  -0.4714   0.06824   0.06502  -0.0341   1.0000   0.0479
  -7.000  -0.4688   0.06373   0.06047  -0.0374   1.0000   0.0495
  -6.750  -0.4649   0.05906   0.05572  -0.0404   1.0000   0.0515
  -6.250  -0.4563   0.04830   0.04439  -0.0457   1.0000   0.0575
  -6.000  -0.4434   0.04565   0.04180  -0.0449   1.0000   0.0593
  -5.750  -0.4300   0.04301   0.03906  -0.0444   1.0000   0.0624
  -5.500  -0.4171   0.03920   0.03471  -0.0450   1.0000   0.0706
  -5.250  -0.4018   0.03654   0.03211  -0.0441   1.0000   0.0731
  -5.000  -0.3853   0.03422   0.02934  -0.0438   1.0000   0.0839
  -4.750  -0.3531   0.02423   0.01803  -0.0413   1.0000   0.0305
  -4.500  -0.3314   0.02167   0.01511  -0.0404   1.0000   0.0300
  -4.250  -0.3094   0.02063   0.01375  -0.0393   1.0000   0.0313
  -4.000  -0.2869   0.01903   0.01190  -0.0383   1.0000   0.0315
  -3.750  -0.2639   0.01731   0.01000  -0.0374   1.0000   0.0312
  -3.500  -0.2411   0.01607   0.00865  -0.0364   1.0000   0.0314
  -3.250  -0.2057   0.01460   0.00713  -0.0380   0.9967   0.0325
  -3.000  -0.1637   0.01330   0.00582  -0.0411   0.9909   0.0374
  -2.750  -0.1206   0.01170   0.00461  -0.0444   0.9851   0.1181
  -2.500  -0.0826   0.01005   0.00430  -0.0478   0.9778   0.4330
  -2.250  -0.0454   0.00930   0.00452  -0.0493   0.9707   0.6913
  -2.000  -0.0090   0.00916   0.00445  -0.0504   0.9602   0.7594
  -1.750   0.0282   0.00903   0.00434  -0.0515   0.9505   0.8044
  -1.500   0.0635   0.00888   0.00421  -0.0521   0.9401   0.8402
  -1.250   0.0956   0.00874   0.00402  -0.0520   0.9272   0.8694
  -1.000   0.1235   0.00859   0.00384  -0.0511   0.9111   0.8956
  -0.750   0.1513   0.00845   0.00365  -0.0501   0.8935   0.9210
  -0.500   0.1841   0.00833   0.00345  -0.0503   0.8757   0.9459
  -0.250   0.2258   0.00822   0.00322  -0.0526   0.8578   0.9672
   0.000   0.2707   0.00816   0.00302  -0.0558   0.8361   0.9859
   0.250   0.3113   0.00813   0.00284  -0.0584   0.8143   1.0000
   0.500   0.3307   0.00820   0.00277  -0.0569   0.7904   1.0000
   0.750   0.3538   0.00831   0.00274  -0.0561   0.7682   1.0000
   1.000   0.3789   0.00845   0.00272  -0.0556   0.7468   1.0000
   1.250   0.4049   0.00860   0.00275  -0.0552   0.7260   1.0000
   1.500   0.4312   0.00876   0.00278  -0.0548   0.7059   1.0000
   1.750   0.4578   0.00893   0.00283  -0.0545   0.6872   1.0000
   2.000   0.4844   0.00910   0.00291  -0.0543   0.6680   1.0000
   2.250   0.5111   0.00929   0.00301  -0.0540   0.6498   1.0000
   2.500   0.5378   0.00948   0.00312  -0.0537   0.6323   1.0000
   2.750   0.5645   0.00967   0.00325  -0.0534   0.6144   1.0000
   3.000   0.5912   0.00986   0.00340  -0.0532   0.5968   1.0000
   3.250   0.6179   0.01006   0.00355  -0.0529   0.5797   1.0000
   3.500   0.6445   0.01028   0.00374  -0.0526   0.5628   1.0000
   3.750   0.6710   0.01049   0.00392  -0.0523   0.5452   1.0000
   4.000   0.6974   0.01070   0.00412  -0.0520   0.5263   1.0000
   4.250   0.7237   0.01092   0.00433  -0.0516   0.5079   1.0000
   4.500   0.7498   0.01117   0.00457  -0.0513   0.4895   1.0000
   4.750   0.7759   0.01138   0.00482  -0.0509   0.4684   1.0000
   5.000   0.8016   0.01164   0.00506  -0.0505   0.4464   1.0000
   5.250   0.8271   0.01189   0.00532  -0.0500   0.4220   1.0000
   5.500   0.8525   0.01216   0.00563  -0.0496   0.3957   1.0000
   5.750   0.8773   0.01248   0.00593  -0.0490   0.3660   1.0000
   6.000   0.9016   0.01286   0.00627  -0.0485   0.3304   1.0000
   6.250   0.9248   0.01337   0.00666  -0.0478   0.2869   1.0000
   6.500   0.9469   0.01406   0.00715  -0.0472   0.2360   1.0000
   6.750   0.9682   0.01492   0.00778  -0.0465   0.1806   1.0000
   7.000   0.9886   0.01596   0.00854  -0.0458   0.1247   1.0000
   7.250   1.0046   0.01774   0.00983  -0.0445   0.0566   1.0000
   7.500   1.0176   0.02004   0.01201  -0.0424   0.0318   1.0000
   7.750   1.0362   0.02136   0.01348  -0.0410   0.0276   1.0000
   8.000   1.0530   0.02289   0.01508  -0.0396   0.0251   1.0000
   8.250   1.0652   0.02543   0.01766  -0.0376   0.0230   1.0000
   8.500   1.0859   0.02652   0.01896  -0.0366   0.0214   1.0000
   8.750   1.1046   0.02833   0.02092  -0.0354   0.0204   1.0000
   9.000   1.1233   0.03042   0.02320  -0.0341   0.0197   1.0000
   9.250   1.1413   0.03283   0.02584  -0.0329   0.0193   1.0000
   9.500   1.1574   0.03562   0.02893  -0.0315   0.0192   1.0000
   9.750   1.1700   0.03884   0.03253  -0.0299   0.0193   1.0000
  10.000   1.1770   0.04255   0.03666  -0.0279   0.0196   1.0000
  10.250   1.1778   0.04654   0.04108  -0.0257   0.0202   1.0000
  10.500   1.1727   0.05058   0.04549  -0.0234   0.0207   1.0000
  10.750   1.1609   0.05433   0.04953  -0.0207   0.0211   1.0000
  11.000   1.1452   0.05807   0.05351  -0.0185   0.0215   1.0000
  11.250   1.1275   0.06221   0.05787  -0.0176   0.0218   1.0000
  11.500   1.1086   0.06693   0.06279  -0.0181   0.0221   1.0000
  11.750   1.0891   0.07229   0.06834  -0.0199   0.0223   1.0000
  12.000   1.0682   0.07857   0.07478  -0.0230   0.0225   1.0000
  12.250   0.9504   0.08155   0.07817  -0.0239   0.0218   1.0000
  12.500   0.9244   0.08974   0.08652  -0.0285   0.0219   1.0000
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