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CLARK YM-18 AIRFOIL (clarym18-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CLARK YM-18 AIRFOIL (clarym18-il)
Reynolds number: 50,000
Max Cl/Cd: 25.68 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarym18-il-50000-n5.txt
Download as CSV file: xf-clarym18-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK YM-18 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5063   0.08391   0.07613  -0.0632   1.0000   0.0967
 -10.500  -0.5688   0.07640   0.06862  -0.0643   1.0000   0.0963
 -10.250  -0.6236   0.07220   0.06440  -0.0614   1.0000   0.0958
 -10.000  -0.6730   0.06933   0.06148  -0.0562   1.0000   0.0955
  -9.750  -0.7094   0.06454   0.05640  -0.0543   0.9963   0.0957
  -9.500  -0.7251   0.05845   0.04968  -0.0557   0.9864   0.0968
  -9.250  -0.7018   0.05663   0.04786  -0.0572   0.9806   0.0987
  -9.000  -0.6859   0.05458   0.04568  -0.0578   0.9731   0.1011
  -8.750  -0.6705   0.05174   0.04248  -0.0590   0.9666   0.1041
  -8.500  -0.6642   0.04867   0.03886  -0.0584   0.9580   0.1070
  -8.250  -0.6369   0.04717   0.03733  -0.0598   0.9525   0.1100
  -8.000  -0.6183   0.04584   0.03589  -0.0595   0.9448   0.1134
  -7.750  -0.5968   0.04386   0.03348  -0.0601   0.9384   0.1181
  -7.500  -0.5722   0.04271   0.03230  -0.0605   0.9320   0.1220
  -7.250  -0.5500   0.04168   0.03117  -0.0605   0.9245   0.1269
  -7.000  -0.5204   0.04029   0.02951  -0.0617   0.9195   0.1331
  -6.750  -0.5009   0.03964   0.02889  -0.0609   0.9114   0.1381
  -6.500  -0.4739   0.03854   0.02749  -0.0615   0.9050   0.1455
  -6.250  -0.4396   0.03785   0.02690  -0.0632   0.9007   0.1529
  -6.000  -0.4244   0.03714   0.02599  -0.0614   0.8914   0.1600
  -5.750  -0.3936   0.03656   0.02549  -0.0624   0.8857   0.1684
  -5.500  -0.3651   0.03591   0.02476  -0.0629   0.8799   0.1780
  -5.250  -0.3452   0.03549   0.02431  -0.0619   0.8716   0.1876
  -5.000  -0.3124   0.03493   0.02377  -0.0630   0.8664   0.1996
  -4.750  -0.2895   0.03454   0.02337  -0.0625   0.8592   0.2123
  -4.500  -0.2653   0.03418   0.02297  -0.0621   0.8518   0.2271
  -4.250  -0.2313   0.03372   0.02253  -0.0633   0.8470   0.2463
  -4.000  -0.2126   0.03354   0.02234  -0.0620   0.8385   0.2637
  -3.750  -0.1857   0.03325   0.02208  -0.0620   0.8318   0.2845
  -3.500  -0.1502   0.03283   0.02170  -0.0634   0.8275   0.3092
  -3.250  -0.1352   0.03281   0.02171  -0.0615   0.8179   0.3285
  -3.000  -0.1053   0.03252   0.02148  -0.0620   0.8118   0.3541
  -2.750  -0.0687   0.03212   0.02112  -0.0634   0.8078   0.3846
  -2.500  -0.0586   0.03224   0.02136  -0.0607   0.7970   0.4066
  -2.250  -0.0274   0.03191   0.02116  -0.0611   0.7915   0.4414
  -2.000  -0.0033   0.03172   0.02116  -0.0603   0.7845   0.4765
  -1.750   0.0171   0.03157   0.02120  -0.0588   0.7753   0.5146
  -1.500   0.0559   0.03086   0.02073  -0.0596   0.7701   0.5702
  -1.250   0.0692   0.03079   0.02090  -0.0564   0.7572   0.6192
  -1.000   0.1100   0.03006   0.02040  -0.0566   0.7512   0.6932
  -0.750   0.1278   0.03017   0.02067  -0.0538   0.7384   0.7544
  -0.500   0.1788   0.02975   0.02027  -0.0557   0.7327   0.8214
  -0.250   0.2114   0.03009   0.02058  -0.0560   0.7215   0.8720
   0.000   0.2720   0.02989   0.02022  -0.0607   0.7153   0.9141
   0.250   0.3275   0.02996   0.02015  -0.0655   0.7065   0.9466
   0.500   0.3947   0.02975   0.01980  -0.0724   0.6980   0.9709
   0.750   0.4631   0.02934   0.01921  -0.0796   0.6903   0.9915
   1.000   0.4942   0.02930   0.01908  -0.0808   0.6788   1.0000
   1.250   0.5043   0.02934   0.01901  -0.0779   0.6679   1.0000
   1.500   0.5234   0.02915   0.01869  -0.0763   0.6582   1.0000
   1.750   0.5283   0.02940   0.01887  -0.0726   0.6457   1.0000
   2.000   0.5582   0.02900   0.01832  -0.0724   0.6375   1.0000
   2.250   0.5600   0.02942   0.01868  -0.0683   0.6240   1.0000
   2.500   0.5805   0.02935   0.01850  -0.0667   0.6137   1.0000
   2.750   0.5983   0.02937   0.01842  -0.0648   0.6024   1.0000
   3.000   0.6084   0.02967   0.01864  -0.0618   0.5897   1.0000
   3.250   0.6417   0.02931   0.01814  -0.0620   0.5810   1.0000
   3.500   0.6472   0.02983   0.01862  -0.0585   0.5673   1.0000
   3.750   0.6669   0.03000   0.01868  -0.0570   0.5564   1.0000
   4.000   0.6904   0.03006   0.01865  -0.0560   0.5459   1.0000
   4.250   0.7028   0.03055   0.01908  -0.0535   0.5339   1.0000
   4.500   0.7355   0.03039   0.01878  -0.0538   0.5251   1.0000
   4.750   0.7425   0.03116   0.01953  -0.0508   0.5129   1.0000
   5.000   0.7746   0.03112   0.01936  -0.0511   0.5050   1.0000
   5.250   0.7812   0.03200   0.02024  -0.0482   0.4941   1.0000
   5.500   0.8166   0.03195   0.02006  -0.0490   0.4872   1.0000
   5.750   0.8181   0.03306   0.02121  -0.0455   0.4768   1.0000
   6.000   0.8508   0.03313   0.02117  -0.0460   0.4700   1.0000
   6.250   0.8547   0.03427   0.02235  -0.0429   0.4612   1.0000
   6.500   0.8781   0.03473   0.02277  -0.0423   0.4544   1.0000
   6.750   0.9003   0.03530   0.02330  -0.0417   0.4481   1.0000
   7.000   0.9052   0.03656   0.02462  -0.0390   0.4404   1.0000
   7.250   0.9349   0.03680   0.02482  -0.0392   0.4348   1.0000
   7.500   0.9426   0.03805   0.02611  -0.0370   0.4281   1.0000
   7.750   0.9509   0.03932   0.02743  -0.0351   0.4215   1.0000
   8.000   0.9828   0.03946   0.02753  -0.0354   0.4165   1.0000
   8.250   0.9818   0.04127   0.02943  -0.0327   0.4099   1.0000
   8.500   0.9863   0.04285   0.03108  -0.0307   0.4034   1.0000
   8.750   1.0207   0.04278   0.03096  -0.0311   0.3986   1.0000
   9.000   1.0099   0.04536   0.03366  -0.0280   0.3920   1.0000
   9.250   1.0074   0.04758   0.03598  -0.0259   0.3853   1.0000
   9.500   1.0466   0.04702   0.03538  -0.0264   0.3808   1.0000
   9.750   1.0140   0.05157   0.04010  -0.0228   0.3732   1.0000
  10.000   1.0070   0.05450   0.04312  -0.0212   0.3663   1.0000
  10.250   1.0556   0.05284   0.04143  -0.0216   0.3626   1.0000
  10.500   0.9567   0.06488   0.05373  -0.0185   0.3497   1.0000
  10.750   0.9913   0.06386   0.05273  -0.0178   0.3459   1.0000
  11.000   1.0524   0.06033   0.04914  -0.0176   0.3435   1.0000
  11.250   0.9387   0.07597   0.06502  -0.0173   0.3273   1.0000
  11.500   0.9861   0.07294   0.06200  -0.0160   0.3253   1.0000
  12.000   0.9196   0.08794   0.07718  -0.0174   0.3035   1.0000
  12.500   0.8599   0.10342   0.09281  -0.0207   0.2786   1.0000
  12.750   0.8791   0.10366   0.09310  -0.0199   0.2733   1.0000
  13.000   0.9117   0.10161   0.09108  -0.0182   0.2706   1.0000
  13.500   0.8836   0.11269   0.10227  -0.0208   0.2507   1.0000
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