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CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CLARK YH AIRFOIL (clarkyh-il)
Reynolds number: 50,000
Max Cl/Cd: 29.06 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkyh-il-50000.txt
Download as CSV file: xf-clarkyh-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK YH AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4921   0.12749   0.12041   0.0007   1.0000   0.2509
 -11.250  -0.4537   0.12031   0.11314   0.0028   1.0000   0.2608
 -11.000  -0.4846   0.12041   0.11340  -0.0006   1.0000   0.2674
 -10.750  -0.4456   0.11337   0.10627   0.0013   1.0000   0.2751
 -10.500  -0.4706   0.11264   0.10567  -0.0015   1.0000   0.2838
 -10.250  -0.4375   0.10682   0.09978   0.0002   1.0000   0.2946
 -10.000  -0.4432   0.10385   0.09688  -0.0010   1.0000   0.3035
  -9.750  -0.4440   0.10130   0.09437  -0.0015   1.0000   0.3160
  -9.500  -0.4263   0.09678   0.08985  -0.0011   1.0000   0.3237
  -9.250  -0.4352   0.09419   0.08735  -0.0020   1.0000   0.3360
  -9.000  -0.4511   0.09249   0.08577  -0.0026   1.0000   0.3507
  -8.750  -0.4404   0.08896   0.08228  -0.0015   1.0000   0.3679
  -8.500  -0.4213   0.08510   0.07842  -0.0002   1.0000   0.3860
  -8.250  -0.4112   0.08188   0.07523   0.0008   1.0000   0.4036
  -8.000  -0.3945   0.07864   0.07198   0.0021   1.0000   0.4240
  -7.750  -0.5308   0.06135   0.05434  -0.0249   1.0000   0.2037
  -7.500  -0.5266   0.05803   0.05097  -0.0230   1.0000   0.1987
  -7.250  -0.5426   0.05272   0.04506  -0.0216   1.0000   0.1864
  -7.000  -0.5370   0.04969   0.04190  -0.0196   1.0000   0.1848
  -6.750  -0.5326   0.04675   0.03868  -0.0175   1.0000   0.1847
  -6.500  -0.5264   0.04398   0.03550  -0.0156   1.0000   0.1857
  -6.250  -0.5172   0.04135   0.03244  -0.0138   1.0000   0.1865
  -6.000  -0.5049   0.03891   0.02960  -0.0122   1.0000   0.1873
  -5.750  -0.4894   0.03716   0.02784  -0.0108   1.0000   0.1904
  -5.500  -0.4738   0.03577   0.02628  -0.0094   1.0000   0.1958
  -5.250  -0.4569   0.03416   0.02421  -0.0082   1.0000   0.2011
  -5.000  -0.4385   0.03269   0.02256  -0.0073   1.0000   0.2060
  -4.750  -0.4187   0.03154   0.02124  -0.0065   1.0000   0.2127
  -4.500  -0.3984   0.03048   0.01998  -0.0059   1.0000   0.2229
  -4.250  -0.3781   0.02960   0.01895  -0.0052   1.0000   0.2369
  -4.000  -0.3572   0.02866   0.01797  -0.0047   1.0000   0.2543
  -3.750  -0.3352   0.02771   0.01702  -0.0043   1.0000   0.2826
  -3.500  -0.3127   0.02682   0.01638  -0.0040   1.0000   0.3285
  -3.250  -0.2683   0.02598   0.01588  -0.0075   0.9923   0.4109
  -3.000  -0.2204   0.02540   0.01579  -0.0118   0.9803   0.5025
  -2.750  -0.0860   0.02432   0.01639  -0.0293   0.9765   1.0000
  -2.500  -0.0308   0.02498   0.01647  -0.0357   0.9615   1.0000
  -2.250   0.0192   0.02560   0.01672  -0.0409   0.9467   1.0000
  -2.000   0.0650   0.02621   0.01706  -0.0453   0.9323   1.0000
  -1.750   0.1088   0.02682   0.01744  -0.0491   0.9183   1.0000
  -1.500   0.1539   0.02740   0.01783  -0.0531   0.9050   1.0000
  -1.250   0.2028   0.02793   0.01820  -0.0576   0.8929   1.0000
  -1.000   0.2286   0.02861   0.01878  -0.0582   0.8792   1.0000
  -0.750   0.2512   0.02937   0.01944  -0.0581   0.8665   1.0000
  -0.500   0.2806   0.03009   0.02007  -0.0592   0.8553   1.0000
  -0.250   0.3155   0.03070   0.02061  -0.0610   0.8451   1.0000
   0.000   0.3231   0.03171   0.02155  -0.0586   0.8333   1.0000
   0.250   0.3460   0.03254   0.02233  -0.0585   0.8235   1.0000
   0.500   0.3785   0.03311   0.02286  -0.0595   0.8127   1.0000
   0.750   0.3883   0.03405   0.02376  -0.0572   0.8001   1.0000
   1.000   0.4085   0.03479   0.02447  -0.0563   0.7880   1.0000
   1.250   0.4409   0.03516   0.02483  -0.0567   0.7752   1.0000
   1.500   0.4840   0.03506   0.02475  -0.0581   0.7624   1.0000
   1.750   0.4980   0.03575   0.02544  -0.0560   0.7482   1.0000
   2.000   0.5182   0.03619   0.02589  -0.0545   0.7337   1.0000
   2.250   0.5373   0.03675   0.02647  -0.0529   0.7202   1.0000
   2.500   0.5590   0.03731   0.02707  -0.0518   0.7083   1.0000
   2.750   0.5940   0.03718   0.02700  -0.0517   0.6969   1.0000
   3.000   0.6204   0.03731   0.02720  -0.0506   0.6838   1.0000
   3.250   0.6394   0.03781   0.02777  -0.0488   0.6692   1.0000
   3.500   0.6610   0.03815   0.02819  -0.0472   0.6543   1.0000
   3.750   0.6858   0.03825   0.02836  -0.0456   0.6387   1.0000
   4.000   0.7136   0.03804   0.02826  -0.0440   0.6221   1.0000
   4.250   0.7439   0.03760   0.02791  -0.0424   0.6047   1.0000
   4.500   0.7752   0.03707   0.02746  -0.0408   0.5869   1.0000
   4.750   0.8059   0.03670   0.02716  -0.0393   0.5689   1.0000
   5.000   0.8148   0.03809   0.02864  -0.0368   0.5466   1.0000
   5.250   0.8341   0.03877   0.02938  -0.0350   0.5278   1.0000
   5.500   0.8540   0.03948   0.03016  -0.0333   0.5111   1.0000
   5.750   0.8709   0.04063   0.03141  -0.0318   0.4964   1.0000
   6.000   0.8916   0.04157   0.03244  -0.0306   0.4841   1.0000
   6.250   0.9295   0.04077   0.03167  -0.0299   0.4721   1.0000
   6.500   0.9403   0.04222   0.03328  -0.0281   0.4578   1.0000
   6.750   0.9500   0.04371   0.03489  -0.0262   0.4436   1.0000
   7.000   0.9714   0.04387   0.03515  -0.0245   0.4283   1.0000
   7.250   0.9970   0.04356   0.03492  -0.0229   0.4124   1.0000
   7.500   1.0120   0.04446   0.03598  -0.0212   0.3981   1.0000
   7.750   1.0303   0.04506   0.03672  -0.0195   0.3834   1.0000
   8.000   1.0847   0.04172   0.03328  -0.0189   0.3599   1.0000
   8.250   1.0908   0.04214   0.03387  -0.0159   0.3368   1.0000
   8.500   1.1244   0.03869   0.03002  -0.0135   0.2987   1.0000
   8.750   1.1333   0.03901   0.03013  -0.0104   0.2655   1.0000
   9.000   1.1415   0.04066   0.03145  -0.0076   0.2295   1.0000
   9.250   1.1461   0.04317   0.03377  -0.0049   0.1994   1.0000
   9.500   1.1564   0.04534   0.03569  -0.0030   0.1754   1.0000
   9.750   1.1591   0.04749   0.03791  -0.0005   0.1604   1.0000
  10.000   1.1598   0.04976   0.04038   0.0020   0.1496   1.0000
  10.250   1.1571   0.05248   0.04333   0.0045   0.1418   1.0000
  10.500   1.1703   0.05433   0.04506   0.0057   0.1330   1.0000
  10.750   1.1559   0.05783   0.04894   0.0086   0.1300   1.0000
  11.000   1.1443   0.06140   0.05278   0.0107   0.1271   1.0000
  11.250   1.1644   0.06341   0.05464   0.0112   0.1206   1.0000
  11.500   1.1407   0.06784   0.05940   0.0128   0.1200   1.0000
  11.750   1.1142   0.07298   0.06481   0.0134   0.1198   1.0000
  12.000   1.0849   0.07898   0.07104   0.0128   0.1202   1.0000
  12.250   1.0544   0.08591   0.07814   0.0111   0.1208   1.0000
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