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DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il)
Reynolds number: 50,000
Max Cl/Cd: 31.36 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du84132v-il-50000.txt
Download as CSV file: xf-du84132v-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DELFT DU84-132V3 AIRFOIL (MEASURED)             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3347   0.10653   0.09967  -0.0240   1.0000   0.3179
  -8.250  -0.3312   0.10429   0.09748  -0.0222   1.0000   0.3275
  -8.000  -0.3399   0.10227   0.09558  -0.0203   1.0000   0.3352
  -7.750  -0.3437   0.10055   0.09394  -0.0180   1.0000   0.3461
  -7.500  -0.3480   0.09820   0.09167  -0.0160   1.0000   0.3527
  -7.250  -0.3855   0.09892   0.09261  -0.0119   1.0000   0.3661
  -7.000  -0.3628   0.09447   0.08814  -0.0110   1.0000   0.3695
  -6.750  -0.3632   0.09215   0.08589  -0.0089   1.0000   0.3741
  -6.500  -0.3872   0.09121   0.08509  -0.0052   1.0000   0.3856
  -6.250  -0.5595   0.06538   0.05886  -0.0359   1.0000   0.1653
  -6.000  -0.5580   0.05857   0.05155  -0.0389   1.0000   0.1491
  -5.750  -0.5467   0.05437   0.04699  -0.0398   1.0000   0.1419
  -5.500  -0.5329   0.04999   0.04217  -0.0411   1.0000   0.1362
  -5.250  -0.5120   0.04576   0.03686  -0.0431   1.0000   0.1297
  -5.000  -0.4926   0.04311   0.03396  -0.0430   1.0000   0.1286
  -4.750  -0.4720   0.04077   0.03128  -0.0430   1.0000   0.1280
  -4.500  -0.4505   0.03882   0.02896  -0.0429   1.0000   0.1285
  -4.250  -0.4284   0.03727   0.02698  -0.0426   1.0000   0.1302
  -4.000  -0.4089   0.03567   0.02540  -0.0421   1.0000   0.1339
  -3.750  -0.3885   0.03454   0.02416  -0.0414   1.0000   0.1379
  -3.500  -0.3675   0.03351   0.02293  -0.0405   1.0000   0.1423
  -3.250  -0.3469   0.03258   0.02183  -0.0394   1.0000   0.1473
  -3.000  -0.3284   0.03177   0.02114  -0.0380   1.0000   0.1558
  -2.750  -0.3097   0.03104   0.02050  -0.0366   1.0000   0.1705
  -2.500  -0.2914   0.03029   0.01994  -0.0353   1.0000   0.1996
  -2.250  -0.2679   0.02743   0.01921  -0.0354   1.0000   0.4408
  -2.000  -0.2864   0.02815   0.02137  -0.0226   1.0000   0.7016
  -1.750  -0.2916   0.02924   0.02233  -0.0145   1.0000   0.7905
  -1.500  -0.2959   0.02936   0.02234  -0.0072   1.0000   0.8443
  -1.250  -0.2993   0.02900   0.02194   0.0001   1.0000   0.8954
  -1.000  -0.1797   0.03072   0.02312  -0.0152   1.0000   1.0000
  -0.750  -0.1815   0.03035   0.02259  -0.0129   1.0000   1.0000
  -0.500  -0.1642   0.03061   0.02262  -0.0138   0.9953   1.0000
  -0.250  -0.1163   0.03198   0.02365  -0.0198   0.9807   1.0000
   0.000  -0.0769   0.03296   0.02436  -0.0240   0.9668   1.0000
   0.250  -0.0486   0.03356   0.02477  -0.0261   0.9551   1.0000
   0.500  -0.0192   0.03430   0.02533  -0.0283   0.9436   1.0000
   0.750   0.0144   0.03521   0.02606  -0.0311   0.9317   1.0000
   1.000   0.0520   0.03623   0.02691  -0.0344   0.9191   1.0000
   1.250   0.0926   0.03724   0.02778  -0.0380   0.9047   1.0000
   1.500   0.1310   0.03810   0.02850  -0.0410   0.8891   1.0000
   1.750   0.1692   0.03888   0.02918  -0.0438   0.8728   1.0000
   2.000   0.2070   0.03963   0.02983  -0.0463   0.8567   1.0000
   2.250   0.2435   0.04032   0.03044  -0.0486   0.8402   1.0000
   2.500   0.2752   0.04095   0.03102  -0.0500   0.8234   1.0000
   2.750   0.3070   0.04156   0.03160  -0.0514   0.8063   1.0000
   3.000   0.3395   0.04219   0.03220  -0.0528   0.7897   1.0000
   3.250   0.3712   0.04290   0.03290  -0.0542   0.7745   1.0000
   3.500   0.4023   0.04366   0.03366  -0.0554   0.7593   1.0000
   3.750   0.4335   0.04441   0.03441  -0.0566   0.7441   1.0000
   4.000   0.4655   0.04508   0.03510  -0.0577   0.7287   1.0000
   4.250   0.4994   0.04566   0.03571  -0.0588   0.7137   1.0000
   4.500   0.5312   0.04633   0.03640  -0.0598   0.6992   1.0000
   4.750   0.5591   0.04717   0.03729  -0.0604   0.6849   1.0000
   5.000   0.5874   0.04796   0.03813  -0.0609   0.6707   1.0000
   5.250   0.6137   0.04884   0.03906  -0.0612   0.6566   1.0000
   5.500   0.6352   0.05001   0.04030  -0.0612   0.6426   1.0000
   5.750   0.6543   0.05138   0.04171  -0.0610   0.6289   1.0000
   6.000   0.6721   0.05286   0.04325  -0.0609   0.6155   1.0000
   6.250   0.6899   0.05437   0.04481  -0.0607   0.6025   1.0000
   6.500   0.7140   0.05541   0.04594  -0.0606   0.5902   1.0000
   6.750   0.7667   0.05423   0.04490  -0.0615   0.5802   1.0000
   7.000   0.7582   0.05787   0.04856  -0.0605   0.5666   1.0000
   7.250   0.7604   0.06062   0.05137  -0.0598   0.5534   1.0000
   7.500   0.7836   0.06164   0.05250  -0.0594   0.5410   1.0000
   7.750   0.8917   0.05416   0.04533  -0.0596   0.5303   1.0000
   8.000   1.0299   0.04479   0.03627  -0.0636   0.5132   1.0000
   8.250   0.8945   0.05937   0.05068  -0.0571   0.4998   1.0000
   8.500   1.0942   0.04374   0.03547  -0.0621   0.4776   1.0000
   8.750   1.1137   0.04409   0.03594  -0.0604   0.4598   1.0000
   9.000   1.1971   0.04028   0.03211  -0.0637   0.4331   1.0000
   9.250   1.2019   0.04140   0.03337  -0.0605   0.4126   1.0000
   9.500   1.2468   0.04060   0.03245  -0.0609   0.3836   1.0000
   9.750   1.2803   0.04083   0.03245  -0.0605   0.3526   1.0000
  10.000   1.2788   0.04250   0.03425  -0.0566   0.3307   1.0000
  10.250   1.3076   0.04279   0.03422  -0.0559   0.3031   1.0000
  10.500   1.3123   0.04448   0.03601  -0.0531   0.2848   1.0000
  10.750   1.3212   0.04623   0.03781  -0.0508   0.2684   1.0000
  11.000   1.3350   0.04801   0.03961  -0.0492   0.2532   1.0000
  11.250   1.3513   0.04998   0.04160  -0.0480   0.2393   1.0000
  11.500   1.3374   0.05265   0.04459  -0.0437   0.2314   1.0000
  11.750   1.3409   0.05491   0.04695  -0.0413   0.2210   1.0000
  12.000   1.3559   0.05660   0.04862  -0.0400   0.2086   1.0000
  12.250   1.3280   0.06028   0.05265  -0.0356   0.2050   1.0000
  12.500   1.0029   0.10242   0.09525  -0.0451   0.2455   1.0000
  12.750   0.9947   0.10870   0.10156  -0.0469   0.2390   1.0000
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