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HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/8 AIRFOIL (hq358-il)
Reynolds number: 50,000
Max Cl/Cd: 43.3 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq358-il-50000-n5.txt
Download as CSV file: xf-hq358-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/8 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3563   0.10741   0.10067  -0.0339   1.0000   0.0821
  -8.250  -0.3679   0.10643   0.09994  -0.0352   1.0000   0.0833
  -8.000  -0.3795   0.10526   0.09892  -0.0355   1.0000   0.0837
  -7.750  -0.3662   0.10003   0.09364  -0.0334   1.0000   0.0856
  -7.500  -0.3621   0.09685   0.09052  -0.0317   1.0000   0.0881
  -7.250  -0.3668   0.09469   0.08847  -0.0304   1.0000   0.0904
  -7.000  -0.3731   0.09263   0.08652  -0.0297   1.0000   0.0926
  -6.750  -0.3828   0.09087   0.08489  -0.0314   1.0000   0.0960
  -6.500  -0.3933   0.08909   0.08317  -0.0384   1.0000   0.0976
  -6.250  -0.3884   0.08498   0.07918  -0.0330   1.0000   0.0994
  -6.000  -0.3863   0.08211   0.07636  -0.0314   1.0000   0.1016
  -5.750  -0.3845   0.07923   0.07352  -0.0316   1.0000   0.1046
  -5.250  -0.3764   0.07260   0.06691  -0.0361   1.0000   0.1145
  -5.000  -0.3457   0.06551   0.05942  -0.0436   1.0000   0.0547
  -4.750  -0.3208   0.06020   0.05371  -0.0491   1.0000   0.0435
  -4.500  -0.3111   0.05679   0.05035  -0.0481   1.0000   0.0408
  -4.250  -0.2920   0.05302   0.04640  -0.0501   1.0000   0.0397
  -4.000  -0.2684   0.04928   0.04237  -0.0526   1.0000   0.0396
  -3.750  -0.2416   0.04573   0.03843  -0.0551   1.0000   0.0403
  -3.500  -0.2129   0.04240   0.03464  -0.0573   1.0000   0.0409
  -3.250  -0.1745   0.03890   0.03061  -0.0609   0.9968   0.0407
  -3.000  -0.1352   0.03577   0.02693  -0.0640   0.9933   0.0400
  -2.750  -0.0961   0.03303   0.02361  -0.0665   0.9896   0.0399
  -2.500  -0.0571   0.03076   0.02071  -0.0686   0.9862   0.0404
  -2.250  -0.0213   0.02889   0.01833  -0.0696   0.9820   0.0417
  -2.000   0.0130   0.02736   0.01646  -0.0703   0.9777   0.0435
  -1.750   0.0471   0.02624   0.01519  -0.0716   0.9736   0.0516
  -1.500   0.0795   0.02532   0.01405  -0.0725   0.9680   0.0623
  -1.250   0.1172   0.02434   0.01294  -0.0746   0.9634   0.0940
  -1.000   0.1502   0.02126   0.01240  -0.0760   0.9617   0.6790
  -0.750   0.1706   0.02053   0.01179  -0.0731   0.9522   1.0000
  -0.500   0.2077   0.02088   0.01159  -0.0753   0.9458   1.0000
  -0.250   0.2415   0.02120   0.01151  -0.0770   0.9379   1.0000
   0.000   0.2758   0.02153   0.01151  -0.0787   0.9304   1.0000
   0.250   0.3118   0.02187   0.01152  -0.0807   0.9228   1.0000
   0.500   0.3435   0.02218   0.01161  -0.0819   0.9137   1.0000
   0.750   0.3807   0.02248   0.01173  -0.0840   0.9060   1.0000
   1.000   0.4138   0.02276   0.01187  -0.0853   0.8965   1.0000
   1.250   0.4456   0.02304   0.01204  -0.0863   0.8864   1.0000
   1.500   0.4805   0.02327   0.01220  -0.0878   0.8770   1.0000
   1.750   0.5177   0.02343   0.01232  -0.0896   0.8679   1.0000
   2.000   0.5508   0.02355   0.01243  -0.0905   0.8557   1.0000
   2.250   0.5876   0.02345   0.01236  -0.0916   0.8419   1.0000
   2.500   0.6245   0.02321   0.01215  -0.0925   0.8272   1.0000
   2.750   0.6561   0.02307   0.01206  -0.0925   0.8115   1.0000
   3.000   0.6857   0.02303   0.01209  -0.0923   0.7963   1.0000
   3.250   0.7154   0.02299   0.01222  -0.0921   0.7814   1.0000
   3.500   0.7450   0.02291   0.01226  -0.0918   0.7656   1.0000
   3.750   0.7753   0.02278   0.01225  -0.0915   0.7492   1.0000
   4.000   0.8065   0.02257   0.01219  -0.0912   0.7320   1.0000
   4.250   0.8318   0.02257   0.01234  -0.0901   0.7099   1.0000
   4.500   0.8597   0.02246   0.01249  -0.0892   0.6866   1.0000
   4.750   0.8875   0.02236   0.01255  -0.0883   0.6599   1.0000
   5.000   0.9145   0.02232   0.01265  -0.0872   0.6286   1.0000
   5.250   0.9412   0.02235   0.01278  -0.0861   0.5923   1.0000
   5.500   0.9669   0.02252   0.01297  -0.0848   0.5514   1.0000
   5.750   0.9911   0.02289   0.01343  -0.0834   0.5077   1.0000
   6.000   1.0135   0.02350   0.01397  -0.0819   0.4655   1.0000
   6.250   1.0345   0.02430   0.01471  -0.0805   0.4273   1.0000
   6.500   1.0549   0.02520   0.01560  -0.0791   0.3937   1.0000
   6.750   1.0747   0.02617   0.01662  -0.0777   0.3623   1.0000
   7.000   1.0936   0.02719   0.01774  -0.0763   0.3319   1.0000
   7.250   1.1111   0.02825   0.01892  -0.0747   0.3019   1.0000
   7.500   1.1267   0.02940   0.02029  -0.0729   0.2712   1.0000
   7.750   1.1350   0.03064   0.02157  -0.0703   0.2296   1.0000
   8.000   1.1363   0.03210   0.02283  -0.0673   0.1582   1.0000
   8.250   1.1342   0.03524   0.02494  -0.0647   0.0714   1.0000
   8.500   1.1379   0.03826   0.02771  -0.0623   0.0428   1.0000
   8.750   1.1420   0.04088   0.03038  -0.0598   0.0341   1.0000
   9.000   1.1468   0.04337   0.03313  -0.0573   0.0299   1.0000
   9.250   1.1504   0.04595   0.03590  -0.0551   0.0274   1.0000
   9.500   1.1523   0.04887   0.03898  -0.0529   0.0258   1.0000
   9.750   1.1597   0.05176   0.04214  -0.0510   0.0246   1.0000
  10.000   1.1699   0.05479   0.04554  -0.0493   0.0236   1.0000
  10.250   1.1784   0.05816   0.04930  -0.0477   0.0228   1.0000
  10.500   1.1823   0.06184   0.05337  -0.0462   0.0223   1.0000
  10.750   1.1808   0.06581   0.05772  -0.0449   0.0220   1.0000
  11.000   1.1745   0.07002   0.06228  -0.0440   0.0217   1.0000
  11.250   1.1645   0.07460   0.06719  -0.0438   0.0216   1.0000
  11.500   1.1517   0.07962   0.07250  -0.0443   0.0215   1.0000
  11.750   1.1369   0.08516   0.07832  -0.0457   0.0216   1.0000
  12.000   1.1204   0.09134   0.08473  -0.0482   0.0217   1.0000
  12.250   1.1033   0.09816   0.09176  -0.0516   0.0219   1.0000
  12.500   1.0861   0.10572   0.09949  -0.0561   0.0222   1.0000
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