Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 200,000
Max Cl/Cd: 68.34 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-200000-n5.txt
Download as CSV file: xf-hq2090sm-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ-2.0/9  9.0%   smoothed                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4714   0.08829   0.08475  -0.0276   1.0000   0.0123
  -9.000  -0.4765   0.08284   0.07935  -0.0305   1.0000   0.0119
  -8.750  -0.4861   0.07628   0.07287  -0.0343   1.0000   0.0115
  -8.500  -0.5024   0.06737   0.06409  -0.0409   1.0000   0.0108
  -8.250  -0.5120   0.06063   0.05731  -0.0465   1.0000   0.0106
  -8.000  -0.5203   0.05539   0.05196  -0.0488   1.0000   0.0105
  -7.750  -0.5275   0.05036   0.04680  -0.0495   1.0000   0.0104
  -7.500  -0.5330   0.04536   0.04159  -0.0492   1.0000   0.0103
  -7.250  -0.5367   0.04046   0.03640  -0.0480   1.0000   0.0103
  -7.000  -0.5312   0.03521   0.03069  -0.0478   0.9983   0.0103
  -6.750  -0.5060   0.02942   0.02416  -0.0507   0.9922   0.0103
  -6.500  -0.4769   0.02532   0.01937  -0.0527   0.9873   0.0106
  -6.250  -0.4485   0.02213   0.01566  -0.0540   0.9823   0.0111
  -6.000  -0.4164   0.02050   0.01379  -0.0556   0.9783   0.0120
  -5.750  -0.3841   0.01950   0.01260  -0.0569   0.9741   0.0136
  -5.500  -0.3520   0.01828   0.01113  -0.0580   0.9695   0.0157
  -5.250  -0.3197   0.01658   0.00925  -0.0592   0.9660   0.0173
  -5.000  -0.2900   0.01573   0.00833  -0.0598   0.9598   0.0197
  -4.750  -0.2571   0.01512   0.00758  -0.0609   0.9551   0.0242
  -4.500  -0.2269   0.01426   0.00667  -0.0618   0.9495   0.0313
  -4.250  -0.1965   0.01368   0.00601  -0.0624   0.9431   0.0391
  -4.000  -0.1640   0.01324   0.00550  -0.0635   0.9385   0.0483
  -3.750  -0.1363   0.01272   0.00496  -0.0636   0.9304   0.0564
  -3.500  -0.1050   0.01228   0.00447  -0.0644   0.9252   0.0688
  -3.250  -0.0779   0.01187   0.00411  -0.0644   0.9168   0.0920
  -2.750  -0.0224   0.01078   0.00347  -0.0650   0.9024   0.2302
  -2.500   0.0026   0.00979   0.00328  -0.0650   0.8957   0.4438
  -2.250   0.0274   0.00942   0.00326  -0.0643   0.8875   0.5567
  -2.000   0.0542   0.00928   0.00324  -0.0638   0.8805   0.6173
  -1.750   0.0808   0.00922   0.00320  -0.0632   0.8725   0.6583
  -1.500   0.1071   0.00917   0.00318  -0.0625   0.8645   0.6946
  -1.250   0.1326   0.00911   0.00316  -0.0616   0.8562   0.7319
  -1.000   0.1575   0.00906   0.00314  -0.0606   0.8465   0.7604
  -0.750   0.1844   0.00902   0.00306  -0.0601   0.8380   0.7740
  -0.500   0.2113   0.00899   0.00299  -0.0597   0.8293   0.7854
   0.000   0.2650   0.00894   0.00288  -0.0588   0.8128   0.8084
   0.250   0.2911   0.00891   0.00286  -0.0583   0.8024   0.8204
   0.500   0.3172   0.00887   0.00282  -0.0576   0.7900   0.8333
   0.750   0.3431   0.00883   0.00276  -0.0569   0.7761   0.8477
   1.000   0.3692   0.00880   0.00274  -0.0563   0.7634   0.8640
   1.250   0.3959   0.00878   0.00274  -0.0558   0.7524   0.8835
   1.500   0.4243   0.00875   0.00273  -0.0556   0.7406   0.9077
   1.750   0.4573   0.00873   0.00272  -0.0565   0.7266   0.9391
   2.000   0.4949   0.00873   0.00272  -0.0586   0.7092   0.9996
   2.250   0.5215   0.00882   0.00277  -0.0583   0.6917   1.0000
   2.500   0.5481   0.00893   0.00282  -0.0580   0.6732   1.0000
   2.750   0.5745   0.00905   0.00290  -0.0577   0.6527   1.0000
   3.000   0.6006   0.00919   0.00301  -0.0573   0.6290   1.0000
   3.250   0.6263   0.00937   0.00311  -0.0568   0.6003   1.0000
   3.500   0.6516   0.00959   0.00323  -0.0563   0.5659   1.0000
   3.750   0.6759   0.00989   0.00338  -0.0556   0.5247   1.0000
   4.000   0.6985   0.01034   0.00361  -0.0546   0.4685   1.0000
   4.250   0.7201   0.01093   0.00389  -0.0536   0.4058   1.0000
   4.500   0.7427   0.01148   0.00422  -0.0529   0.3534   1.0000
   4.750   0.7654   0.01204   0.00459  -0.0522   0.3068   1.0000
   5.000   0.7879   0.01264   0.00499  -0.0515   0.2632   1.0000
   5.250   0.8111   0.01318   0.00544  -0.0510   0.2274   1.0000
   5.500   0.8344   0.01372   0.00588  -0.0504   0.1945   1.0000
   5.750   0.8575   0.01429   0.00635  -0.0498   0.1637   1.0000
   6.000   0.8801   0.01493   0.00687  -0.0492   0.1301   1.0000
   6.250   0.9018   0.01567   0.00747  -0.0485   0.0979   1.0000
   6.500   0.9240   0.01638   0.00812  -0.0478   0.0779   1.0000
   6.750   0.9460   0.01710   0.00888  -0.0470   0.0653   1.0000
   7.000   0.9677   0.01783   0.00960  -0.0463   0.0532   1.0000
   7.250   0.9896   0.01850   0.01027  -0.0456   0.0419   1.0000
   7.500   1.0106   0.01930   0.01110  -0.0448   0.0349   1.0000
   7.750   1.0321   0.02001   0.01190  -0.0440   0.0277   1.0000
   8.000   1.0520   0.02091   0.01286  -0.0429   0.0205   1.0000
   8.250   1.0699   0.02206   0.01404  -0.0417   0.0163   1.0000
   8.500   1.0879   0.02315   0.01533  -0.0404   0.0141   1.0000
   8.750   1.1050   0.02430   0.01660  -0.0390   0.0126   1.0000
   9.000   1.1194   0.02571   0.01810  -0.0374   0.0114   1.0000
   9.250   1.1343   0.02705   0.01960  -0.0359   0.0104   1.0000
   9.500   1.1490   0.02836   0.02109  -0.0343   0.0094   1.0000
   9.750   1.1615   0.02992   0.02284  -0.0326   0.0089   1.0000
  10.000   1.1721   0.03158   0.02468  -0.0306   0.0084   1.0000
  10.250   1.1801   0.03329   0.02657  -0.0284   0.0081   1.0000
  10.500   1.1860   0.03510   0.02857  -0.0261   0.0077   1.0000
  10.750   1.1897   0.03713   0.03081  -0.0238   0.0075   1.0000
  11.000   1.1909   0.03937   0.03326  -0.0217   0.0073   1.0000
  11.250   1.1886   0.04204   0.03616  -0.0196   0.0071   1.0000
  11.500   1.1845   0.04498   0.03940  -0.0179   0.0070   1.0000
  11.750   1.1776   0.04827   0.04294  -0.0166   0.0070   1.0000
  12.000   1.1661   0.05225   0.04718  -0.0159   0.0069   1.0000
  12.250   1.1533   0.05664   0.05182  -0.0159   0.0068   1.0000
  12.500   1.1406   0.06127   0.05669  -0.0168   0.0068   1.0000
  12.750   1.1262   0.06654   0.06219  -0.0186   0.0068   1.0000
  13.000   1.1085   0.07289   0.06876  -0.0215   0.0068   1.0000
  13.250   1.0925   0.07958   0.07566  -0.0253   0.0068   1.0000
  13.500   1.0757   0.08723   0.08350  -0.0302   0.0068   1.0000
  13.750   1.0585   0.09579   0.09224  -0.0358   0.0069   1.0000
  14.000   1.0382   0.10593   0.10252  -0.0424   0.0070   1.0000
  14.250   1.0055   0.12081   0.11761  -0.0517   0.0073   1.0000
<< Back to HQ-2.0/9 9.0% smoothed (hq2090sm-il)

Polar data table (+)

Polar graphs


<< Back to HQ-2.0/9 9.0% smoothed (hq2090sm-il)