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CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il)
Reynolds number: 100,000
Max Cl/Cd: 45.83 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cast102-il-100000.txt
Download as CSV file: xf-cast102-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CAST 10-2/DOA 2 AIRFOIL                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4062   0.10279   0.09819  -0.0365   1.0000   0.1139
  -9.750  -0.4373   0.09900   0.09449  -0.0386   1.0000   0.1154
  -9.500  -0.4694   0.09462   0.09019  -0.0407   1.0000   0.1158
  -9.250  -0.4261   0.09293   0.08848  -0.0336   1.0000   0.1229
  -9.000  -0.4397   0.08953   0.08513  -0.0332   1.0000   0.1268
  -8.750  -0.4685   0.08511   0.08079  -0.0344   1.0000   0.1290
  -8.500  -0.5011   0.08048   0.07621  -0.0353   1.0000   0.1295
  -8.250  -0.5320   0.07686   0.07262  -0.0340   1.0000   0.1294
  -8.000  -0.5627   0.07398   0.06975  -0.0311   1.0000   0.1292
  -7.750  -0.5948   0.07091   0.06664  -0.0286   1.0000   0.1297
  -7.500  -0.6323   0.06847   0.06400  -0.0260   1.0000   0.1309
  -7.250  -0.6159   0.06316   0.05888  -0.0246   1.0000   0.1362
  -7.000  -0.6233   0.06016   0.05583  -0.0225   1.0000   0.1421
  -6.750  -0.6914   0.06716   0.06161  -0.0225   1.0000   0.1473
  -6.500  -0.6743   0.06149   0.05638  -0.0213   1.0000   0.1529
  -6.250  -0.6718   0.05852   0.05327  -0.0200   1.0000   0.1665
  -6.000  -0.6652   0.05569   0.05038  -0.0186   1.0000   0.1823
  -5.750  -0.6566   0.05305   0.04773  -0.0171   1.0000   0.2013
  -5.000  -0.6324   0.04577   0.04036  -0.0120   1.0000   0.3019
  -4.750  -0.6208   0.04304   0.03800  -0.0086   1.0000   0.3375
  -4.500  -0.6057   0.04059   0.03559  -0.0067   1.0000   0.3681
  -4.250  -0.5078   0.03571   0.02694  -0.0138   1.0000   0.1009
  -4.000  -0.4787   0.03252   0.02341  -0.0131   1.0000   0.0847
  -3.750  -0.4511   0.03026   0.02079  -0.0123   1.0000   0.0768
  -3.500  -0.4255   0.02992   0.02003  -0.0110   1.0000   0.0733
  -3.250  -0.3997   0.02822   0.01820  -0.0105   1.0000   0.0738
  -3.000  -0.3743   0.02709   0.01697  -0.0099   1.0000   0.0737
  -2.750  -0.3491   0.02620   0.01599  -0.0092   1.0000   0.0732
  -2.500  -0.3236   0.02508   0.01490  -0.0087   1.0000   0.0736
  -2.250  -0.2983   0.02402   0.01395  -0.0083   1.0000   0.0751
  -2.000  -0.2736   0.02330   0.01336  -0.0082   1.0000   0.0799
  -1.750  -0.2484   0.02288   0.01288  -0.0080   1.0000   0.0854
  -1.500  -0.2219   0.02239   0.01234  -0.0082   1.0000   0.0914
  -1.250  -0.1947   0.02204   0.01198  -0.0085   1.0000   0.1058
  -1.000  -0.1686   0.02020   0.01290  -0.0074   1.0000   0.7450
  -0.750  -0.1661   0.02075   0.01364   0.0001   1.0000   0.8169
  -0.500  -0.1646   0.02106   0.01402   0.0074   1.0000   0.8618
  -0.250  -0.1634   0.02119   0.01419   0.0144   1.0000   0.9019
   0.000  -0.1548   0.02125   0.01423   0.0193   1.0000   0.9365
   0.250  -0.1100   0.02190   0.01479   0.0167   1.0000   0.9807
   0.500  -0.0618   0.02243   0.01521   0.0113   1.0000   0.9948
   0.750  -0.0396   0.02242   0.01515   0.0104   1.0000   1.0000
   1.000  -0.0334   0.02212   0.01482   0.0123   1.0000   1.0000
   1.250  -0.0161   0.02215   0.01480   0.0122   1.0000   1.0000
   1.500   0.0310   0.02284   0.01542   0.0066   0.9920   1.0000
   1.750   0.0938   0.02369   0.01622  -0.0016   0.9759   1.0000
   2.000   0.1474   0.02428   0.01677  -0.0078   0.9615   1.0000
   2.250   0.1988   0.02469   0.01719  -0.0133   0.9469   1.0000
   2.500   0.2498   0.02496   0.01747  -0.0184   0.9319   1.0000
   2.750   0.3006   0.02505   0.01761  -0.0231   0.9166   1.0000
   3.000   0.3516   0.02493   0.01755  -0.0275   0.9010   1.0000
   3.250   0.4013   0.02462   0.01733  -0.0314   0.8857   1.0000
   3.500   0.4502   0.02412   0.01693  -0.0348   0.8707   1.0000
   3.750   0.4982   0.02341   0.01635  -0.0378   0.8556   1.0000
   4.000   0.5483   0.02239   0.01550  -0.0406   0.8401   1.0000
   4.250   0.6020   0.02091   0.01420  -0.0435   0.8237   1.0000
   4.500   0.6343   0.01970   0.01316  -0.0427   0.7997   1.0000
   4.750   0.6682   0.01818   0.01178  -0.0416   0.7683   1.0000
   5.000   0.6914   0.01701   0.01069  -0.0387   0.7098   1.0000
   5.250   0.7497   0.01636   0.00856  -0.0406   0.4555   1.0000
   5.500   0.7653   0.01768   0.00918  -0.0386   0.3758   1.0000
   5.750   0.7857   0.01877   0.00989  -0.0376   0.3305   1.0000
   6.000   0.8088   0.01978   0.01065  -0.0370   0.2994   1.0000
   6.250   0.8335   0.02079   0.01144  -0.0368   0.2758   1.0000
   6.500   0.8575   0.02164   0.01228  -0.0365   0.2544   1.0000
   6.750   0.8808   0.02248   0.01305  -0.0360   0.2350   1.0000
   7.000   0.9018   0.02326   0.01372  -0.0353   0.2156   1.0000
   7.250   0.9210   0.02391   0.01440  -0.0342   0.1966   1.0000
   7.500   0.9415   0.02467   0.01521  -0.0333   0.1797   1.0000
   7.750   0.9603   0.02544   0.01600  -0.0321   0.1618   1.0000
   8.000   0.9779   0.02640   0.01689  -0.0308   0.1422   1.0000
   8.250   0.9927   0.02757   0.01811  -0.0288   0.1179   1.0000
   8.500   1.0101   0.02895   0.01933  -0.0275   0.1003   1.0000
   8.750   1.0322   0.03051   0.02096  -0.0267   0.0889   1.0000
   9.000   1.0557   0.03233   0.02296  -0.0261   0.0810   1.0000
   9.250   1.0805   0.03427   0.02474  -0.0263   0.0748   1.0000
   9.500   1.1022   0.03644   0.02735  -0.0252   0.0713   1.0000
   9.750   1.1226   0.03880   0.03002  -0.0242   0.0683   1.0000
  10.000   1.1403   0.04087   0.03228  -0.0231   0.0656   1.0000
  10.250   1.1588   0.04417   0.03564  -0.0227   0.0630   1.0000
  10.500   1.1629   0.04675   0.03877  -0.0195   0.0618   1.0000
  10.750   1.1641   0.05007   0.04257  -0.0163   0.0611   1.0000
  11.000   1.1601   0.05366   0.04660  -0.0128   0.0609   1.0000
  11.250   1.1505   0.05738   0.05072  -0.0090   0.0609   1.0000
  11.500   1.1346   0.06095   0.05461  -0.0047   0.0610   1.0000
  11.750   1.1155   0.06476   0.05871  -0.0008   0.0612   1.0000
  12.000   1.0941   0.06888   0.06309   0.0022   0.0615   1.0000
  12.250   1.0714   0.07339   0.06782   0.0044   0.0619   1.0000
  12.500   1.0481   0.07837   0.07299   0.0055   0.0623   1.0000
  12.750   1.0254   0.08391   0.07867   0.0055   0.0627   1.0000
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