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HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il)
Reynolds number: 50,000
Max Cl/Cd: 37.57 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2195-il-50000-n5.txt
Download as CSV file: xf-hq2195-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4581   0.12003   0.11258  -0.0202   1.0000   0.1176
 -10.250  -0.4602   0.11707   0.10968  -0.0222   1.0000   0.1230
 -10.000  -0.4746   0.10744   0.10008  -0.0314   1.0000   0.0682
  -9.750  -0.4671   0.10353   0.09619  -0.0315   1.0000   0.0675
  -9.500  -0.4630   0.09962   0.09232  -0.0322   1.0000   0.0667
  -9.250  -0.4602   0.09570   0.08844  -0.0332   1.0000   0.0654
  -9.000  -0.4599   0.09161   0.08443  -0.0346   1.0000   0.0637
  -8.750  -0.4635   0.08710   0.08000  -0.0368   1.0000   0.0619
  -8.500  -0.4716   0.08214   0.07513  -0.0399   1.0000   0.0600
  -8.000  -0.5130   0.06975   0.06261  -0.0498   1.0000   0.0552
  -7.750  -0.5129   0.06606   0.05888  -0.0498   1.0000   0.0548
  -7.500  -0.5135   0.06234   0.05508  -0.0497   1.0000   0.0544
  -7.250  -0.5130   0.05864   0.05122  -0.0495   1.0000   0.0541
  -7.000  -0.5107   0.05501   0.04738  -0.0491   1.0000   0.0539
  -6.750  -0.5062   0.05147   0.04357  -0.0485   1.0000   0.0537
  -6.500  -0.4993   0.04809   0.03982  -0.0478   1.0000   0.0541
  -6.250  -0.4894   0.04498   0.03617  -0.0470   1.0000   0.0552
  -6.000  -0.4776   0.04209   0.03306  -0.0462   1.0000   0.0566
  -5.750  -0.4631   0.03978   0.03058  -0.0452   1.0000   0.0580
  -5.500  -0.4467   0.03735   0.02777  -0.0443   1.0000   0.0587
  -5.250  -0.4286   0.03510   0.02517  -0.0434   1.0000   0.0596
  -5.000  -0.4092   0.03310   0.02283  -0.0425   1.0000   0.0608
  -4.750  -0.3889   0.03138   0.02080  -0.0415   1.0000   0.0630
  -4.500  -0.3679   0.02994   0.01898  -0.0405   1.0000   0.0667
  -4.250  -0.3467   0.02852   0.01731  -0.0394   1.0000   0.0697
  -4.000  -0.3261   0.02727   0.01602  -0.0382   1.0000   0.0725
  -3.750  -0.3053   0.02623   0.01487  -0.0369   1.0000   0.0762
  -3.500  -0.2842   0.02544   0.01386  -0.0356   1.0000   0.0824
  -3.250  -0.2638   0.02456   0.01302  -0.0347   1.0000   0.0906
  -3.000  -0.2425   0.02377   0.01211  -0.0337   1.0000   0.0994
  -2.750  -0.2204   0.02300   0.01135  -0.0333   1.0000   0.1168
  -2.500  -0.1961   0.02205   0.01053  -0.0334   0.9997   0.1495
  -2.250  -0.1685   0.01964   0.01013  -0.0348   0.9969   0.4880
  -2.000  -0.1496   0.01957   0.01058  -0.0316   0.9910   0.6884
  -1.750  -0.1339   0.01967   0.01089  -0.0276   0.9847   0.7863
  -1.500  -0.1206   0.01959   0.01098  -0.0225   0.9784   0.8861
  -1.250  -0.0573   0.01944   0.01062  -0.0286   0.9755   0.9934
  -1.000  -0.0210   0.01963   0.01050  -0.0318   0.9696   1.0000
  -0.750   0.0101   0.01975   0.01037  -0.0338   0.9617   1.0000
  -0.500   0.0496   0.02002   0.01038  -0.0371   0.9553   1.0000
  -0.250   0.0821   0.02021   0.01037  -0.0390   0.9461   1.0000
   0.000   0.1208   0.02046   0.01044  -0.0418   0.9374   1.0000
   0.250   0.1613   0.02068   0.01051  -0.0447   0.9274   1.0000
   0.500   0.1979   0.02085   0.01057  -0.0468   0.9157   1.0000
   0.750   0.2360   0.02102   0.01064  -0.0490   0.9044   1.0000
   1.000   0.2778   0.02115   0.01071  -0.0518   0.8942   1.0000
   1.250   0.3157   0.02127   0.01081  -0.0538   0.8830   1.0000
   1.500   0.3492   0.02141   0.01094  -0.0549   0.8710   1.0000
   1.750   0.3834   0.02152   0.01105  -0.0560   0.8591   1.0000
   2.000   0.4190   0.02158   0.01115  -0.0573   0.8474   1.0000
   2.250   0.4561   0.02158   0.01121  -0.0586   0.8357   1.0000
   2.500   0.4888   0.02160   0.01130  -0.0591   0.8220   1.0000
   2.750   0.5204   0.02160   0.01137  -0.0593   0.8072   1.0000
   3.000   0.5520   0.02156   0.01144  -0.0594   0.7917   1.0000
   3.250   0.5788   0.02159   0.01158  -0.0587   0.7730   1.0000
   3.500   0.6077   0.02154   0.01164  -0.0581   0.7538   1.0000
   3.750   0.6386   0.02139   0.01163  -0.0577   0.7341   1.0000
   4.000   0.6644   0.02137   0.01173  -0.0566   0.7095   1.0000
   4.250   0.6912   0.02129   0.01177  -0.0556   0.6826   1.0000
   4.500   0.7166   0.02124   0.01186  -0.0543   0.6505   1.0000
   4.750   0.7426   0.02114   0.01181  -0.0529   0.6128   1.0000
   5.000   0.7684   0.02107   0.01168  -0.0513   0.5681   1.0000
   5.250   0.7934   0.02122   0.01161  -0.0497   0.5192   1.0000
   5.500   0.8157   0.02171   0.01189  -0.0480   0.4712   1.0000
   5.750   0.8357   0.02243   0.01240  -0.0465   0.4259   1.0000
   6.000   0.8545   0.02323   0.01308  -0.0449   0.3831   1.0000
   6.250   0.8723   0.02410   0.01386  -0.0434   0.3408   1.0000
   6.500   0.8890   0.02505   0.01475  -0.0418   0.2961   1.0000
   6.750   0.9042   0.02614   0.01569  -0.0402   0.2484   1.0000
   7.000   0.9189   0.02744   0.01676  -0.0386   0.2044   1.0000
   7.250   0.9343   0.02891   0.01802  -0.0372   0.1686   1.0000
   7.500   0.9504   0.03047   0.01943  -0.0359   0.1434   1.0000
   7.750   0.9674   0.03205   0.02098  -0.0348   0.1237   1.0000
   8.000   0.9849   0.03367   0.02257  -0.0338   0.1086   1.0000
   8.250   1.0038   0.03534   0.02432  -0.0328   0.0966   1.0000
   8.500   1.0236   0.03712   0.02623  -0.0319   0.0870   1.0000
   8.750   1.0441   0.03909   0.02817  -0.0312   0.0807   1.0000
   9.000   1.0652   0.04120   0.03066  -0.0304   0.0742   1.0000
   9.250   1.0827   0.04315   0.03268  -0.0295   0.0690   1.0000
   9.500   1.1025   0.04581   0.03559  -0.0288   0.0656   1.0000
   9.750   1.1182   0.04878   0.03902  -0.0277   0.0629   1.0000
  10.000   1.1290   0.05166   0.04226  -0.0263   0.0603   1.0000
  10.250   1.1377   0.05422   0.04503  -0.0250   0.0576   1.0000
  10.500   1.1479   0.05707   0.04787  -0.0242   0.0551   1.0000
  10.750   1.1418   0.06054   0.05190  -0.0219   0.0541   1.0000
  11.000   1.1314   0.06416   0.05591  -0.0195   0.0535   1.0000
  11.250   1.1169   0.06806   0.06015  -0.0177   0.0532   1.0000
  11.500   1.0990   0.07239   0.06476  -0.0168   0.0530   1.0000
  11.750   1.0782   0.07732   0.06995  -0.0171   0.0529   1.0000
  12.000   1.0553   0.08299   0.07581  -0.0186   0.0531   1.0000
  12.250   1.0302   0.08968   0.08268  -0.0217   0.0533   1.0000
  12.500   1.0044   0.09754   0.09068  -0.0263   0.0537   1.0000
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