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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 200,000
Max Cl/Cd: 78.14 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2511-il-200000.txt
Download as CSV file: xf-hq2511-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/11 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4007   0.08920   0.08577  -0.0423   1.0000   0.0490
  -9.000  -0.4010   0.08584   0.08246  -0.0431   1.0000   0.0498
  -8.750  -0.4033   0.08249   0.07917  -0.0439   1.0000   0.0506
  -8.500  -0.4100   0.07888   0.07562  -0.0449   1.0000   0.0514
  -8.250  -0.4226   0.07537   0.07221  -0.0456   1.0000   0.0519
  -8.000  -0.4482   0.07279   0.06975  -0.0442   1.0000   0.0518
  -7.750  -0.4832   0.07047   0.06752  -0.0422   1.0000   0.0515
  -7.500  -0.5076   0.06815   0.06522  -0.0402   1.0000   0.0515
  -7.250  -0.4955   0.06169   0.05857  -0.0483   0.9946   0.0532
  -6.750  -0.4696   0.03560   0.03036  -0.0626   0.9775   0.0277
  -6.500  -0.4420   0.03081   0.02520  -0.0650   0.9733   0.0266
  -6.250  -0.4090   0.02677   0.02060  -0.0674   0.9704   0.0260
  -6.000  -0.3831   0.02410   0.01750  -0.0676   0.9642   0.0258
  -5.750  -0.3494   0.02184   0.01483  -0.0689   0.9605   0.0265
  -5.500  -0.3120   0.02020   0.01291  -0.0708   0.9579   0.0275
  -5.250  -0.2819   0.01863   0.01135  -0.0717   0.9531   0.0304
  -5.000  -0.2493   0.01778   0.01036  -0.0726   0.9480   0.0357
  -4.750  -0.2127   0.01684   0.00950  -0.0748   0.9449   0.0536
  -4.500  -0.1723   0.01643   0.00901  -0.0775   0.9428   0.0694
  -4.250  -0.1463   0.01586   0.00844  -0.0775   0.9357   0.0777
  -4.000  -0.1116   0.01533   0.00786  -0.0790   0.9316   0.0879
  -3.750  -0.0749   0.01475   0.00728  -0.0810   0.9288   0.1017
  -3.500  -0.0494   0.01424   0.00686  -0.0809   0.9214   0.1212
  -3.250  -0.0188   0.01308   0.00628  -0.0821   0.9163   0.2326
  -3.000   0.0033   0.01175   0.00624  -0.0814   0.9103   0.5531
  -2.750   0.0301   0.01171   0.00631  -0.0807   0.9034   0.6243
  -2.500   0.0626   0.01166   0.00623  -0.0809   0.8994   0.6639
  -2.250   0.0865   0.01173   0.00627  -0.0797   0.8911   0.6919
  -2.000   0.1161   0.01169   0.00621  -0.0794   0.8861   0.7162
  -1.750   0.1410   0.01174   0.00624  -0.0783   0.8791   0.7373
  -1.500   0.1670   0.01175   0.00625  -0.0773   0.8733   0.7579
  -1.250   0.1939   0.01175   0.00623  -0.0764   0.8689   0.7809
  -1.000   0.2153   0.01182   0.00633  -0.0747   0.8610   0.7991
  -0.750   0.2423   0.01175   0.00625  -0.0740   0.8563   0.8142
  -0.500   0.2660   0.01177   0.00625  -0.0729   0.8492   0.8278
  -0.250   0.2926   0.01167   0.00613  -0.0723   0.8428   0.8405
   0.000   0.3173   0.01160   0.00604  -0.0713   0.8350   0.8526
   0.250   0.3434   0.01144   0.00587  -0.0705   0.8276   0.8629
   0.500   0.3680   0.01136   0.00580  -0.0695   0.8191   0.8739
   0.750   0.3946   0.01121   0.00563  -0.0688   0.8120   0.8857
   1.000   0.4186   0.01113   0.00556  -0.0678   0.8026   0.8987
   1.250   0.4459   0.01095   0.00536  -0.0671   0.7949   0.9124
   1.500   0.4729   0.01081   0.00524  -0.0666   0.7843   0.9281
   1.750   0.5054   0.01070   0.00515  -0.0673   0.7749   0.9450
   2.000   0.5452   0.01056   0.00500  -0.0695   0.7669   0.9620
   2.250   0.5871   0.01048   0.00495  -0.0725   0.7558   0.9833
   2.500   0.6206   0.01045   0.00490  -0.0741   0.7450   1.0000
   2.750   0.6464   0.01044   0.00485  -0.0738   0.7330   1.0000
   3.000   0.6730   0.01041   0.00478  -0.0736   0.7183   1.0000
   3.250   0.6994   0.01040   0.00472  -0.0732   0.7015   1.0000
   3.500   0.7257   0.01041   0.00471  -0.0728   0.6838   1.0000
   3.750   0.7521   0.01045   0.00470  -0.0723   0.6659   1.0000
   4.000   0.7779   0.01052   0.00475  -0.0718   0.6457   1.0000
   4.250   0.8033   0.01062   0.00481  -0.0712   0.6229   1.0000
   4.500   0.8280   0.01075   0.00491  -0.0705   0.5962   1.0000
   4.750   0.8521   0.01093   0.00502  -0.0697   0.5653   1.0000
   5.000   0.8752   0.01120   0.00517  -0.0687   0.5295   1.0000
   5.250   0.8968   0.01160   0.00539  -0.0675   0.4895   1.0000
   5.500   0.9176   0.01211   0.00571  -0.0663   0.4502   1.0000
   5.750   0.9382   0.01267   0.00611  -0.0651   0.4132   1.0000
   6.000   0.9587   0.01321   0.00652  -0.0640   0.3740   1.0000
   6.250   0.9783   0.01380   0.00698  -0.0627   0.3363   1.0000
   6.500   0.9967   0.01453   0.00752  -0.0613   0.3033   1.0000
   6.750   1.0148   0.01528   0.00811  -0.0599   0.2723   1.0000
   7.000   1.0336   0.01595   0.00867  -0.0587   0.2427   1.0000
   7.250   1.0530   0.01657   0.00923  -0.0576   0.2168   1.0000
   7.500   1.0718   0.01723   0.00980  -0.0563   0.1957   1.0000
   7.750   1.0915   0.01782   0.01038  -0.0553   0.1772   1.0000
   8.000   1.1104   0.01843   0.01095  -0.0541   0.1592   1.0000
   8.250   1.1283   0.01909   0.01156  -0.0528   0.1422   1.0000
   8.500   1.1475   0.01967   0.01217  -0.0517   0.1201   1.0000
   8.750   1.1593   0.02088   0.01306  -0.0497   0.0691   1.0000
   9.000   1.1646   0.02248   0.01435  -0.0466   0.0425   1.0000
   9.250   1.1733   0.02371   0.01561  -0.0439   0.0368   1.0000
   9.500   1.1788   0.02512   0.01709  -0.0409   0.0339   1.0000
   9.750   1.1870   0.02637   0.01848  -0.0384   0.0322   1.0000
  10.000   1.1938   0.02777   0.01999  -0.0360   0.0307   1.0000
  10.250   1.1999   0.02929   0.02159  -0.0337   0.0293   1.0000
  10.500   1.2027   0.03116   0.02352  -0.0314   0.0276   1.0000
  10.750   1.2048   0.03360   0.02600  -0.0291   0.0264   1.0000
  11.000   1.2153   0.03520   0.02774  -0.0276   0.0259   1.0000
  11.250   1.2262   0.03701   0.02969  -0.0261   0.0253   1.0000
  11.500   1.2377   0.03897   0.03179  -0.0248   0.0247   1.0000
  11.750   1.2495   0.04107   0.03406  -0.0235   0.0243   1.0000
  12.000   1.2600   0.04338   0.03656  -0.0223   0.0239   1.0000
  12.250   1.2672   0.04573   0.03909  -0.0210   0.0232   1.0000
  12.500   1.2723   0.04828   0.04183  -0.0198   0.0227   1.0000
  12.750   1.2743   0.05088   0.04462  -0.0187   0.0220   1.0000
  13.000   1.2748   0.05368   0.04757  -0.0179   0.0214   1.0000
  13.250   1.2726   0.05704   0.05116  -0.0170   0.0213   1.0000
  13.500   1.2667   0.06079   0.05516  -0.0165   0.0212   1.0000
  13.750   1.2575   0.06488   0.05950  -0.0163   0.0212   1.0000
  14.000   1.2453   0.06943   0.06431  -0.0167   0.0212   1.0000
  14.250   1.2297   0.07457   0.06971  -0.0177   0.0214   1.0000
  14.500   1.2116   0.08035   0.07576  -0.0195   0.0215   1.0000
  14.750   1.1881   0.08727   0.08297  -0.0225   0.0219   1.0000
  15.000   1.1624   0.09528   0.09126  -0.0268   0.0222   1.0000
  15.250   1.1350   0.10452   0.10075  -0.0325   0.0225   1.0000
  15.500   1.1058   0.11513   0.11159  -0.0396   0.0229   1.0000
  15.750   1.0730   0.12788   0.12454  -0.0484   0.0234   1.0000
  16.000   1.0310   0.14482   0.14165  -0.0598   0.0245   1.0000
  16.250   0.9947   0.16162   0.15847  -0.0697   0.0259   1.0000
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