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HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il)
Reynolds number: 100,000
Max Cl/Cd: 55.4 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2195-il-100000.txt
Download as CSV file: xf-hq2195-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4596   0.11642   0.11113  -0.0214   1.0000   0.0919
 -10.250  -0.4755   0.11405   0.10886  -0.0270   1.0000   0.0942
 -10.000  -0.4936   0.11126   0.10619  -0.0328   1.0000   0.0947
  -9.750  -0.4525   0.10537   0.10020  -0.0251   1.0000   0.0991
  -9.500  -0.4480   0.10227   0.09711  -0.0258   1.0000   0.1041
  -9.250  -0.4596   0.09915   0.09410  -0.0300   1.0000   0.1079
  -9.000  -0.4861   0.09587   0.09098  -0.0368   1.0000   0.1089
  -8.750  -0.4460   0.09195   0.08695  -0.0291   1.0000   0.1164
  -8.500  -0.4551   0.08874   0.08383  -0.0319   1.0000   0.1214
  -8.250  -0.4847   0.08515   0.08042  -0.0376   1.0000   0.1230
  -8.000  -0.4635   0.08160   0.07686  -0.0332   1.0000   0.1278
  -7.750  -0.4640   0.07887   0.07420  -0.0327   1.0000   0.1323
  -7.500  -0.4990   0.07415   0.06952  -0.0417   1.0000   0.1377
  -7.250  -0.4938   0.07022   0.06567  -0.0398   1.0000   0.1412
  -7.000  -0.4859   0.06799   0.06351  -0.0371   1.0000   0.1469
  -6.750  -0.5098   0.06404   0.05943  -0.0403   1.0000   0.1549
  -6.500  -0.4981   0.06190   0.05742  -0.0362   1.0000   0.1600
  -6.250  -0.5082   0.05869   0.05410  -0.0367   1.0000   0.1708
  -6.000  -0.5028   0.05659   0.05203  -0.0343   1.0000   0.1792
  -5.750  -0.5004   0.05391   0.04934  -0.0328   1.0000   0.1900
  -5.500  -0.4961   0.05150   0.04690  -0.0315   1.0000   0.2051
  -5.000  -0.4450   0.03626   0.02959  -0.0396   1.0000   0.1048
  -4.750  -0.4157   0.03219   0.02419  -0.0388   1.0000   0.0808
  -4.500  -0.3939   0.02904   0.02084  -0.0384   1.0000   0.0789
  -4.250  -0.3706   0.02689   0.01834  -0.0378   1.0000   0.0780
  -4.000  -0.3467   0.02549   0.01657  -0.0371   1.0000   0.0795
  -3.750  -0.3225   0.02390   0.01471  -0.0366   1.0000   0.0818
  -3.500  -0.2989   0.02243   0.01319  -0.0359   1.0000   0.0839
  -3.250  -0.2757   0.02138   0.01206  -0.0352   1.0000   0.0873
  -3.000  -0.2527   0.02059   0.01118  -0.0343   1.0000   0.0927
  -2.750  -0.2302   0.01965   0.01036  -0.0337   1.0000   0.1017
  -2.500  -0.2076   0.01884   0.00960  -0.0329   1.0000   0.1128
  -2.250  -0.1845   0.01811   0.00899  -0.0324   1.0000   0.1386
  -2.000  -0.1648   0.01532   0.00872  -0.0313   1.0000   0.6187
  -1.750  -0.1556   0.01545   0.00915  -0.0264   1.0000   0.7479
  -1.500  -0.1458   0.01559   0.00938  -0.0220   1.0000   0.8090
  -1.250  -0.1354   0.01565   0.00950  -0.0178   0.9988   0.8650
  -1.000  -0.0913   0.01565   0.00956  -0.0198   0.9924   0.9681
  -0.750  -0.0368   0.01601   0.00967  -0.0264   0.9839   1.0000
  -0.500   0.0103   0.01633   0.00977  -0.0313   0.9739   1.0000
  -0.250   0.0571   0.01666   0.00992  -0.0359   0.9640   1.0000
   0.000   0.1091   0.01705   0.01016  -0.0413   0.9557   1.0000
   0.250   0.1457   0.01724   0.01023  -0.0437   0.9453   1.0000
   0.500   0.1878   0.01750   0.01040  -0.0470   0.9363   1.0000
   0.750   0.2328   0.01772   0.01056  -0.0507   0.9277   1.0000
   1.000   0.2692   0.01790   0.01069  -0.0527   0.9170   1.0000
   1.250   0.3138   0.01803   0.01080  -0.0559   0.9077   1.0000
   1.500   0.3590   0.01805   0.01083  -0.0592   0.8980   1.0000
   1.750   0.3973   0.01807   0.01087  -0.0610   0.8862   1.0000
   2.000   0.4423   0.01796   0.01081  -0.0639   0.8755   1.0000
   2.250   0.4937   0.01761   0.01054  -0.0674   0.8666   1.0000
   2.500   0.5297   0.01740   0.01040  -0.0682   0.8530   1.0000
   2.750   0.5658   0.01710   0.01019  -0.0687   0.8388   1.0000
   3.000   0.6010   0.01673   0.00990  -0.0689   0.8236   1.0000
   3.250   0.6353   0.01628   0.00953  -0.0686   0.8072   1.0000
   3.500   0.6627   0.01596   0.00930  -0.0673   0.7853   1.0000
   3.750   0.6940   0.01540   0.00877  -0.0661   0.7626   1.0000
   4.000   0.7207   0.01493   0.00831  -0.0642   0.7325   1.0000
   4.250   0.7442   0.01462   0.00800  -0.0621   0.6934   1.0000
   4.500   0.7680   0.01442   0.00777  -0.0602   0.6474   1.0000
   4.750   0.7915   0.01442   0.00763  -0.0584   0.5951   1.0000
   5.000   0.8144   0.01470   0.00763  -0.0568   0.5427   1.0000
   5.250   0.8364   0.01526   0.00792  -0.0553   0.4947   1.0000
   5.500   0.8576   0.01594   0.00841  -0.0539   0.4501   1.0000
   5.750   0.8779   0.01665   0.00894  -0.0525   0.4061   1.0000
   6.000   0.8964   0.01739   0.00953  -0.0509   0.3539   1.0000
   6.250   0.9117   0.01834   0.01018  -0.0488   0.2850   1.0000
   6.500   0.9250   0.01969   0.01104  -0.0467   0.2090   1.0000
   6.750   0.9402   0.02119   0.01214  -0.0450   0.1636   1.0000
   7.000   0.9572   0.02274   0.01345  -0.0435   0.1356   1.0000
   7.250   0.9756   0.02443   0.01499  -0.0422   0.1152   1.0000
   7.500   0.9965   0.02615   0.01665  -0.0412   0.1000   1.0000
   7.750   1.0209   0.02828   0.01866  -0.0407   0.0902   1.0000
   8.000   1.0442   0.02985   0.02039  -0.0399   0.0822   1.0000
   8.250   1.0696   0.03228   0.02286  -0.0396   0.0766   1.0000
   8.500   1.0932   0.03453   0.02544  -0.0387   0.0729   1.0000
   8.750   1.1149   0.03672   0.02782  -0.0380   0.0693   1.0000
   9.000   1.1352   0.04028   0.03147  -0.0376   0.0656   1.0000
   9.250   1.1484   0.04286   0.03462  -0.0356   0.0643   1.0000
   9.500   1.1587   0.04625   0.03853  -0.0335   0.0635   1.0000
   9.750   1.1647   0.04996   0.04274  -0.0313   0.0630   1.0000
  10.000   1.1651   0.05372   0.04697  -0.0288   0.0622   1.0000
  10.250   1.1605   0.05756   0.05124  -0.0262   0.0616   1.0000
  10.500   1.1508   0.06156   0.05561  -0.0237   0.0614   1.0000
  10.750   1.1350   0.06563   0.05998  -0.0210   0.0616   1.0000
  11.000   1.1136   0.06963   0.06422  -0.0183   0.0621   1.0000
  11.250   1.0913   0.07409   0.06886  -0.0171   0.0628   1.0000
  11.500   1.0680   0.07915   0.07409  -0.0172   0.0635   1.0000
  11.750   1.0459   0.08489   0.07996  -0.0186   0.0643   1.0000
  12.000   1.0275   0.09134   0.08649  -0.0209   0.0651   1.0000
  12.250   0.9441   0.11314   0.10854  -0.0369   0.0797   1.0000
  12.500   0.9561   0.11646   0.11188  -0.0354   0.0788   1.0000
  12.750   0.8578   0.15295   0.14810  -0.0647   0.1352   1.0000
  13.000   0.8948   0.15748   0.15276  -0.0596   0.1321   1.0000
  13.250   0.8559   0.16298   0.15809  -0.0698   0.1287   1.0000
  13.500   0.7275   0.16067   0.15639  -0.0588   0.1319   1.0000
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