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HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/9 AIRFOIL (hq209-il)
Reynolds number: 500,000
Max Cl/Cd: 97.88 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq209-il-500000.txt
Download as CSV file: xf-hq209-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/9 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4542   0.08328   0.08108  -0.0301   1.0000   0.0156
  -8.500  -0.4561   0.07913   0.07696  -0.0322   1.0000   0.0157
  -8.250  -0.4603   0.07483   0.07271  -0.0346   1.0000   0.0163
  -8.000  -0.4692   0.07050   0.06843  -0.0371   1.0000   0.0163
  -7.750  -0.4805   0.06463   0.06258  -0.0430   1.0000   0.0159
  -7.500  -0.4869   0.05975   0.05765  -0.0455   1.0000   0.0163
  -7.250  -0.4947   0.05579   0.05363  -0.0454   1.0000   0.0165
  -7.000  -0.4980   0.05196   0.04971  -0.0452   0.9990   0.0167
  -6.750  -0.4607   0.04689   0.04427  -0.0505   0.9950   0.0196
  -6.500  -0.4349   0.04173   0.03873  -0.0547   0.9898   0.0198
  -6.250  -0.4183   0.03093   0.02729  -0.0601   0.9842   0.0213
  -6.000  -0.3867   0.02778   0.02393  -0.0628   0.9818   0.0222
  -5.750  -0.3606   0.01883   0.01388  -0.0625   0.9756   0.0141
  -5.500  -0.3269   0.01641   0.01108  -0.0638   0.9727   0.0136
  -5.250  -0.2927   0.01465   0.00905  -0.0651   0.9701   0.0135
  -5.000  -0.2628   0.01302   0.00726  -0.0656   0.9651   0.0138
  -4.750  -0.2328   0.01189   0.00603  -0.0661   0.9594   0.0148
  -4.500  -0.2007   0.01118   0.00525  -0.0670   0.9552   0.0167
  -4.250  -0.1739   0.01062   0.00461  -0.0667   0.9471   0.0187
  -4.000  -0.1451   0.00994   0.00387  -0.0669   0.9413   0.0237
  -3.750  -0.1193   0.00940   0.00331  -0.0664   0.9327   0.0377
  -3.500  -0.0918   0.00906   0.00296  -0.0662   0.9262   0.0566
  -3.250  -0.0657   0.00874   0.00270  -0.0659   0.9179   0.0808
  -3.000  -0.0401   0.00820   0.00244  -0.0656   0.9107   0.1550
  -2.750  -0.0163   0.00734   0.00218  -0.0653   0.9025   0.3252
  -2.500   0.0073   0.00665   0.00206  -0.0648   0.8945   0.5110
  -2.250   0.0331   0.00645   0.00201  -0.0642   0.8869   0.5822
  -2.000   0.0594   0.00637   0.00197  -0.0637   0.8781   0.6216
  -1.750   0.0862   0.00633   0.00192  -0.0633   0.8705   0.6498
  -1.500   0.1127   0.00629   0.00189  -0.0628   0.8618   0.6778
  -1.250   0.1391   0.00626   0.00188  -0.0623   0.8528   0.7023
  -1.000   0.1656   0.00624   0.00184  -0.0617   0.8434   0.7230
  -0.750   0.1918   0.00622   0.00183  -0.0611   0.8330   0.7461
  -0.500   0.2183   0.00620   0.00182  -0.0606   0.8233   0.7642
  -0.250   0.2447   0.00618   0.00180  -0.0601   0.8140   0.7820
   0.000   0.2711   0.00616   0.00178  -0.0595   0.8039   0.7985
   0.250   0.2978   0.00612   0.00175  -0.0591   0.7926   0.8104
   0.500   0.3247   0.00610   0.00173  -0.0588   0.7819   0.8219
   0.750   0.3515   0.00608   0.00170  -0.0584   0.7716   0.8343
   1.000   0.3780   0.00606   0.00169  -0.0580   0.7611   0.8479
   1.250   0.4042   0.00602   0.00169  -0.0575   0.7497   0.8634
   1.500   0.4299   0.00598   0.00169  -0.0569   0.7373   0.8829
   1.750   0.4554   0.00592   0.00170  -0.0561   0.7246   0.9097
   2.000   0.4885   0.00589   0.00170  -0.0570   0.7104   0.9538
   2.250   0.5278   0.00593   0.00172  -0.0596   0.6938   1.0000
   2.500   0.5547   0.00603   0.00176  -0.0594   0.6763   1.0000
   2.750   0.5813   0.00615   0.00182  -0.0592   0.6561   1.0000
   3.000   0.6076   0.00629   0.00189  -0.0589   0.6327   1.0000
   3.250   0.6333   0.00647   0.00197  -0.0584   0.6011   1.0000
   3.500   0.6574   0.00678   0.00209  -0.0577   0.5511   1.0000
   3.750   0.6801   0.00724   0.00225  -0.0568   0.4818   1.0000
   4.000   0.7037   0.00769   0.00246  -0.0562   0.4256   1.0000
   4.250   0.7274   0.00816   0.00271  -0.0556   0.3735   1.0000
   4.500   0.7511   0.00864   0.00300  -0.0550   0.3225   1.0000
   4.750   0.7747   0.00914   0.00330  -0.0545   0.2800   1.0000
   5.000   0.7990   0.00958   0.00359  -0.0540   0.2480   1.0000
   5.250   0.8238   0.00996   0.00388  -0.0536   0.2227   1.0000
   5.500   0.8486   0.01033   0.00417  -0.0533   0.1963   1.0000
   5.750   0.8722   0.01084   0.00453  -0.0527   0.1533   1.0000
   6.000   0.8928   0.01171   0.00504  -0.0519   0.0922   1.0000
   6.250   0.9149   0.01241   0.00556  -0.0511   0.0622   1.0000
   6.500   0.9385   0.01293   0.00603  -0.0506   0.0503   1.0000
   6.750   0.9621   0.01342   0.00651  -0.0500   0.0425   1.0000
   7.000   0.9865   0.01381   0.00694  -0.0495   0.0372   1.0000
   7.250   1.0099   0.01430   0.00742  -0.0489   0.0311   1.0000
   7.500   1.0341   0.01468   0.00785  -0.0485   0.0242   1.0000
   7.750   1.0545   0.01557   0.00866  -0.0474   0.0126   1.0000
   8.000   1.0764   0.01624   0.00939  -0.0465   0.0098   1.0000
   8.250   1.0954   0.01727   0.01051  -0.0452   0.0079   1.0000
   8.500   1.1160   0.01803   0.01137  -0.0441   0.0074   1.0000
   8.750   1.1352   0.01893   0.01239  -0.0429   0.0070   1.0000
   9.000   1.1530   0.01994   0.01353  -0.0414   0.0067   1.0000
   9.250   1.1704   0.02096   0.01466  -0.0400   0.0062   1.0000
   9.500   1.1860   0.02211   0.01597  -0.0384   0.0060   1.0000
   9.750   1.2001   0.02337   0.01735  -0.0366   0.0056   1.0000
  10.000   1.2122   0.02482   0.01894  -0.0346   0.0055   1.0000
  10.250   1.2210   0.02656   0.02086  -0.0322   0.0053   1.0000
  10.500   1.2251   0.02854   0.02303  -0.0292   0.0051   1.0000
  10.750   1.2270   0.03062   0.02532  -0.0260   0.0051   1.0000
  11.000   1.2275   0.03281   0.02774  -0.0230   0.0050   1.0000
  11.250   1.2280   0.03492   0.03005  -0.0204   0.0051   1.0000
  11.500   1.2256   0.03735   0.03269  -0.0179   0.0051   1.0000
  11.750   1.2196   0.04022   0.03580  -0.0157   0.0051   1.0000
  12.000   1.2105   0.04349   0.03930  -0.0139   0.0051   1.0000
  12.250   1.2024   0.04679   0.04283  -0.0128   0.0052   1.0000
  12.500   1.1904   0.05078   0.04705  -0.0124   0.0052   1.0000
  12.750   1.1747   0.05566   0.05220  -0.0129   0.0054   1.0000
  13.000   1.1554   0.06146   0.05823  -0.0145   0.0054   1.0000
  13.250   1.1328   0.06854   0.06557  -0.0176   0.0055   1.0000
  13.500   1.1093   0.07664   0.07390  -0.0222   0.0056   1.0000
  13.750   1.0858   0.08583   0.08328  -0.0281   0.0057   1.0000
  14.000   1.0631   0.09594   0.09356  -0.0348   0.0057   1.0000
  14.250   1.0396   0.10730   0.10508  -0.0421   0.0058   1.0000
  14.500   1.0127   0.12032   0.11823  -0.0501   0.0059   1.0000
  14.750   0.8719   0.12861   0.12678  -0.0530   0.0059   1.0000
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