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HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il)
Reynolds number: 500,000
Max Cl/Cd: 79.05 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2195-il-500000-n5.txt
Download as CSV file: xf-hq2195-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.1/9.5 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5079   0.09122   0.08882  -0.0299   1.0000   0.0100
 -10.250  -0.5197   0.08433   0.08197  -0.0334   1.0000   0.0102
  -9.500  -0.7369   0.02920   0.02548  -0.0586   0.9991   0.0107
  -9.250  -0.7146   0.02553   0.02128  -0.0609   0.9933   0.0112
  -9.000  -0.6871   0.02422   0.01984  -0.0623   0.9882   0.0115
  -8.750  -0.6567   0.02340   0.01893  -0.0638   0.9843   0.0119
  -8.500  -0.6281   0.02213   0.01747  -0.0651   0.9794   0.0123
  -8.250  -0.5992   0.02072   0.01584  -0.0663   0.9742   0.0128
  -8.000  -0.5687   0.01928   0.01414  -0.0678   0.9699   0.0133
  -7.750  -0.5400   0.01816   0.01281  -0.0685   0.9633   0.0139
  -7.500  -0.5089   0.01733   0.01180  -0.0697   0.9575   0.0145
  -7.250  -0.4803   0.01610   0.01038  -0.0704   0.9501   0.0150
  -7.000  -0.4512   0.01519   0.00937  -0.0711   0.9424   0.0155
  -6.750  -0.4233   0.01455   0.00865  -0.0714   0.9337   0.0160
  -6.500  -0.3951   0.01398   0.00799  -0.0717   0.9258   0.0165
  -6.250  -0.3686   0.01347   0.00740  -0.0716   0.9165   0.0171
  -6.000  -0.3418   0.01299   0.00683  -0.0715   0.9082   0.0179
  -5.750  -0.3154   0.01252   0.00626  -0.0713   0.8994   0.0185
  -5.500  -0.2892   0.01206   0.00571  -0.0710   0.8912   0.0189
  -5.250  -0.2628   0.01166   0.00522  -0.0708   0.8831   0.0193
  -5.000  -0.2371   0.01107   0.00456  -0.0705   0.8754   0.0201
  -4.750  -0.2105   0.01070   0.00413  -0.0703   0.8683   0.0210
  -4.500  -0.1836   0.01040   0.00380  -0.0702   0.8618   0.0220
  -4.250  -0.1565   0.01016   0.00351  -0.0700   0.8552   0.0233
  -4.000  -0.1292   0.00993   0.00320  -0.0699   0.8492   0.0246
  -3.750  -0.1020   0.00966   0.00289  -0.0698   0.8426   0.0262
  -3.500  -0.0746   0.00942   0.00263  -0.0697   0.8370   0.0292
  -3.250  -0.0469   0.00924   0.00242  -0.0697   0.8316   0.0329
  -3.000  -0.0194   0.00904   0.00223  -0.0696   0.8259   0.0413
  -2.750   0.0080   0.00886   0.00206  -0.0695   0.8184   0.0548
  -2.500   0.0349   0.00866   0.00190  -0.0693   0.8082   0.0772
  -2.250   0.0620   0.00843   0.00176  -0.0692   0.7979   0.1128
  -2.000   0.0888   0.00810   0.00161  -0.0691   0.7891   0.1769
  -1.750   0.1143   0.00732   0.00142  -0.0692   0.7799   0.3632
  -1.500   0.1404   0.00686   0.00137  -0.0691   0.7715   0.4988
  -1.250   0.1675   0.00673   0.00134  -0.0689   0.7636   0.5472
  -1.000   0.1948   0.00662   0.00135  -0.0687   0.7563   0.5935
  -0.750   0.2220   0.00655   0.00139  -0.0685   0.7496   0.6388
  -0.500   0.2494   0.00652   0.00142  -0.0682   0.7430   0.6751
  -0.250   0.2770   0.00652   0.00143  -0.0680   0.7358   0.6927
   0.000   0.3049   0.00652   0.00143  -0.0679   0.7286   0.7025
   0.250   0.3327   0.00653   0.00143  -0.0678   0.7206   0.7112
   0.500   0.3606   0.00655   0.00144  -0.0677   0.7121   0.7201
   0.750   0.3881   0.00657   0.00146  -0.0675   0.7028   0.7282
   1.000   0.4159   0.00659   0.00148  -0.0674   0.6916   0.7367
   1.250   0.4433   0.00661   0.00151  -0.0672   0.6788   0.7456
   1.500   0.4704   0.00666   0.00155  -0.0670   0.6621   0.7543
   1.750   0.4972   0.00672   0.00158  -0.0666   0.6388   0.7638
   2.000   0.5226   0.00687   0.00162  -0.0660   0.5970   0.7740
   2.250   0.5451   0.00727   0.00172  -0.0649   0.5230   0.7849
   2.500   0.5671   0.00780   0.00194  -0.0639   0.4482   0.7967
   2.750   0.5906   0.00821   0.00214  -0.0632   0.3959   0.8098
   3.000   0.6153   0.00847   0.00231  -0.0626   0.3634   0.8239
   3.250   0.6405   0.00868   0.00248  -0.0621   0.3395   0.8388
   3.750   0.6905   0.00901   0.00280  -0.0609   0.3036   0.8727
   4.000   0.7149   0.00916   0.00296  -0.0602   0.2853   0.8939
   4.250   0.7388   0.00936   0.00314  -0.0594   0.2582   0.9246
   4.500   0.7707   0.00975   0.00336  -0.0606   0.2129   1.0000
   4.750   0.7944   0.01028   0.00366  -0.0601   0.1673   1.0000
   5.000   0.8177   0.01087   0.00401  -0.0595   0.1244   1.0000
   5.250   0.8420   0.01133   0.00435  -0.0591   0.0995   1.0000
   5.500   0.8669   0.01172   0.00467  -0.0587   0.0840   1.0000
   5.750   0.8919   0.01209   0.00499  -0.0584   0.0726   1.0000
   6.000   0.9169   0.01245   0.00533  -0.0580   0.0639   1.0000
   6.250   0.9415   0.01284   0.00569  -0.0576   0.0556   1.0000
   6.500   0.9664   0.01319   0.00604  -0.0572   0.0490   1.0000
   6.750   0.9906   0.01360   0.00643  -0.0567   0.0413   1.0000
   7.000   1.0144   0.01406   0.00686  -0.0561   0.0338   1.0000
   7.250   1.0383   0.01450   0.00730  -0.0556   0.0295   1.0000
   7.500   1.0615   0.01501   0.00780  -0.0550   0.0262   1.0000
   7.750   1.0850   0.01545   0.00830  -0.0544   0.0246   1.0000
   8.000   1.1080   0.01593   0.00882  -0.0537   0.0231   1.0000
   8.250   1.1302   0.01649   0.00940  -0.0530   0.0215   1.0000
   8.500   1.1511   0.01717   0.01014  -0.0520   0.0202   1.0000
   8.750   1.1732   0.01768   0.01072  -0.0512   0.0195   1.0000
   9.000   1.1947   0.01823   0.01134  -0.0504   0.0187   1.0000
   9.250   1.2156   0.01881   0.01199  -0.0495   0.0178   1.0000
   9.500   1.2357   0.01944   0.01267  -0.0485   0.0170   1.0000
   9.750   1.2546   0.02015   0.01343  -0.0473   0.0162   1.0000
  10.000   1.2700   0.02114   0.01448  -0.0457   0.0152   1.0000
  10.250   1.2889   0.02176   0.01519  -0.0446   0.0148   1.0000
  10.500   1.3062   0.02246   0.01600  -0.0432   0.0143   1.0000
  10.750   1.3221   0.02320   0.01684  -0.0417   0.0137   1.0000
  11.000   1.3360   0.02394   0.01765  -0.0398   0.0131   1.0000
  11.250   1.3491   0.02468   0.01846  -0.0379   0.0125   1.0000
  11.500   1.3604   0.02554   0.01938  -0.0359   0.0120   1.0000
  11.750   1.3664   0.02679   0.02070  -0.0334   0.0114   1.0000
  12.000   1.3766   0.02777   0.02180  -0.0315   0.0111   1.0000
  12.250   1.3868   0.02879   0.02294  -0.0297   0.0108   1.0000
  12.500   1.3950   0.02999   0.02425  -0.0279   0.0104   1.0000
  12.750   1.4019   0.03134   0.02574  -0.0262   0.0100   1.0000
  13.000   1.4087   0.03274   0.02725  -0.0246   0.0096   1.0000
  13.250   1.4153   0.03421   0.02881  -0.0233   0.0093   1.0000
  13.500   1.4214   0.03578   0.03048  -0.0221   0.0090   1.0000
  13.750   1.4244   0.03770   0.03251  -0.0209   0.0088   1.0000
  14.000   1.4249   0.03995   0.03486  -0.0200   0.0085   1.0000
  14.250   1.4226   0.04264   0.03767  -0.0192   0.0083   1.0000
  14.500   1.4236   0.04511   0.04029  -0.0188   0.0081   1.0000
  14.750   1.4204   0.04819   0.04353  -0.0187   0.0079   1.0000
  15.000   1.4175   0.05142   0.04691  -0.0189   0.0077   1.0000
  15.250   1.4115   0.05522   0.05086  -0.0196   0.0076   1.0000
  15.500   1.4050   0.05936   0.05516  -0.0208   0.0074   1.0000
  15.750   1.3970   0.06404   0.05999  -0.0225   0.0072   1.0000
  16.000   1.3860   0.06959   0.06570  -0.0251   0.0071   1.0000
  16.250   1.3770   0.07520   0.07145  -0.0280   0.0070   1.0000
  16.500   1.3588   0.08278   0.07922  -0.0321   0.0070   1.0000
  16.750   1.3432   0.09022   0.08681  -0.0363   0.0069   1.0000
  17.000   1.3245   0.09847   0.09523  -0.0410   0.0069   1.0000
  17.250   1.3016   0.10779   0.10471  -0.0464   0.0069   1.0000
  17.500   1.2780   0.11755   0.11463  -0.0521   0.0069   1.0000
  17.750   1.2544   0.12762   0.12485  -0.0581   0.0069   1.0000
  18.000   1.2271   0.13899   0.13639  -0.0649   0.0070   1.0000
  18.250   1.1994   0.15102   0.14858  -0.0722   0.0071   1.0000
  18.500   1.1659   0.16522   0.16294  -0.0809   0.0072   1.0000
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