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HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il)
Reynolds number: 100,000
Max Cl/Cd: 60.86 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3510-il-100000-n5.txt
Download as CSV file: xf-hq3510-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/10 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2718   0.09543   0.09116  -0.0359   1.0000   0.0455
  -8.750  -0.2784   0.09305   0.08885  -0.0346   1.0000   0.0458
  -8.500  -0.2863   0.09070   0.08657  -0.0333   1.0000   0.0460
  -8.250  -0.2865   0.08710   0.08301  -0.0344   0.9980   0.0460
  -8.000  -0.3583   0.09253   0.08812  -0.0367   1.0000   0.0443
  -7.750  -0.3733   0.09080   0.08650  -0.0347   1.0000   0.0438
  -7.500  -0.3863   0.08927   0.08506  -0.0320   1.0000   0.0444
  -7.250  -0.3776   0.08463   0.08044  -0.0378   0.9932   0.0441
  -7.000  -0.3568   0.07541   0.07114  -0.0501   0.9847   0.0278
  -6.750  -0.3416   0.06977   0.06547  -0.0569   0.9770   0.0266
  -6.500  -0.3228   0.06344   0.05902  -0.0649   0.9700   0.0253
  -6.250  -0.3030   0.05714   0.05253  -0.0722   0.9624   0.0242
  -6.000  -0.2807   0.05080   0.04588  -0.0784   0.9558   0.0231
  -5.750  -0.2564   0.04469   0.03934  -0.0831   0.9491   0.0222
  -5.500  -0.2243   0.03871   0.03276  -0.0878   0.9454   0.0216
  -5.250  -0.2016   0.03485   0.02840  -0.0889   0.9382   0.0215
  -5.000  -0.1696   0.03148   0.02447  -0.0912   0.9343   0.0219
  -4.750  -0.1344   0.02940   0.02202  -0.0936   0.9316   0.0243
  -4.500  -0.1097   0.02741   0.01959  -0.0933   0.9248   0.0264
  -4.250  -0.0760   0.02510   0.01679  -0.0945   0.9212   0.0273
  -4.000  -0.0404   0.02317   0.01447  -0.0958   0.9187   0.0286
  -3.750  -0.0142   0.02174   0.01285  -0.0954   0.9129   0.0301
  -3.500   0.0159   0.02055   0.01161  -0.0960   0.9083   0.0334
  -3.250   0.0496   0.01958   0.01048  -0.0970   0.9051   0.0408
  -3.000   0.0759   0.01894   0.00986  -0.0969   0.8991   0.0566
  -2.750   0.1061   0.01843   0.00934  -0.0976   0.8941   0.0825
  -2.500   0.1398   0.01773   0.00864  -0.0989   0.8907   0.1070
  -2.250   0.1651   0.01717   0.00819  -0.0986   0.8839   0.1473
  -2.000   0.1918   0.01568   0.00804  -0.0993   0.8793   0.4888
  -1.750   0.2196   0.01545   0.00812  -0.0986   0.8752   0.6371
  -1.500   0.2398   0.01549   0.00825  -0.0965   0.8674   0.7038
  -1.250   0.2647   0.01539   0.00820  -0.0947   0.8630   0.7680
  -1.000   0.2819   0.01535   0.00820  -0.0918   0.8551   0.8135
  -0.750   0.3099   0.01516   0.00795  -0.0913   0.8501   0.8396
  -0.500   0.3359   0.01509   0.00780  -0.0907   0.8428   0.8560
  -0.250   0.3659   0.01493   0.00756  -0.0909   0.8369   0.8747
   0.000   0.3960   0.01480   0.00739  -0.0911   0.8302   0.8983
   0.250   0.4340   0.01465   0.00720  -0.0930   0.8238   0.9334
   0.500   0.4719   0.01454   0.00700  -0.0951   0.8164   1.0000
   0.750   0.5037   0.01445   0.00679  -0.0958   0.8077   1.0000
   1.000   0.5318   0.01442   0.00667  -0.0958   0.7964   1.0000
   1.250   0.5607   0.01435   0.00652  -0.0958   0.7847   1.0000
   1.500   0.5897   0.01427   0.00636  -0.0958   0.7727   1.0000
   1.750   0.6187   0.01422   0.00624  -0.0958   0.7612   1.0000
   2.000   0.6484   0.01419   0.00614  -0.0959   0.7508   1.0000
   2.250   0.6749   0.01427   0.00623  -0.0957   0.7389   1.0000
   2.500   0.7018   0.01434   0.00627  -0.0954   0.7266   1.0000
   2.750   0.7290   0.01440   0.00632  -0.0951   0.7137   1.0000
   3.000   0.7561   0.01446   0.00637  -0.0949   0.7001   1.0000
   3.250   0.7831   0.01453   0.00646  -0.0945   0.6852   1.0000
   3.500   0.8100   0.01460   0.00652  -0.0941   0.6692   1.0000
   3.750   0.8363   0.01471   0.00662  -0.0937   0.6513   1.0000
   4.000   0.8615   0.01485   0.00676  -0.0930   0.6306   1.0000
   4.250   0.8868   0.01500   0.00694  -0.0923   0.6078   1.0000
   4.500   0.9115   0.01518   0.00709  -0.0916   0.5811   1.0000
   4.750   0.9354   0.01543   0.00727  -0.0907   0.5499   1.0000
   5.000   0.9585   0.01575   0.00748  -0.0896   0.5153   1.0000
   5.250   0.9804   0.01618   0.00781  -0.0885   0.4778   1.0000
   5.500   1.0012   0.01671   0.00818  -0.0872   0.4417   1.0000
   5.750   1.0215   0.01730   0.00864  -0.0860   0.4079   1.0000
   6.000   1.0416   0.01793   0.00917  -0.0847   0.3786   1.0000
   6.250   1.0618   0.01856   0.00974  -0.0836   0.3533   1.0000
   6.500   1.0819   0.01922   0.01037  -0.0824   0.3319   1.0000
   6.750   1.1023   0.01986   0.01101  -0.0814   0.3129   1.0000
   7.000   1.1224   0.02053   0.01168  -0.0803   0.2958   1.0000
   7.250   1.1422   0.02121   0.01239  -0.0792   0.2801   1.0000
   7.500   1.1617   0.02192   0.01313  -0.0780   0.2651   1.0000
   7.750   1.1810   0.02262   0.01391  -0.0768   0.2508   1.0000
   8.000   1.1998   0.02333   0.01477  -0.0756   0.2366   1.0000
   8.250   1.2160   0.02408   0.01556  -0.0741   0.2191   1.0000
   8.500   1.2313   0.02477   0.01634  -0.0724   0.1954   1.0000
   8.750   1.2450   0.02555   0.01714  -0.0706   0.1691   1.0000
   9.000   1.2549   0.02654   0.01800  -0.0684   0.1382   1.0000
   9.250   1.2614   0.02796   0.01914  -0.0659   0.0991   1.0000
   9.500   1.2661   0.02974   0.02062  -0.0635   0.0621   1.0000
   9.750   1.2705   0.03161   0.02237  -0.0610   0.0377   1.0000
  10.000   1.2724   0.03371   0.02445  -0.0582   0.0249   1.0000
  10.250   1.2722   0.03598   0.02675  -0.0555   0.0202   1.0000
  10.500   1.2746   0.03799   0.02900  -0.0532   0.0180   1.0000
  10.750   1.2755   0.04016   0.03143  -0.0510   0.0164   1.0000
  11.000   1.2750   0.04251   0.03396  -0.0492   0.0150   1.0000
  11.250   1.2710   0.04527   0.03689  -0.0474   0.0139   1.0000
  11.500   1.2646   0.04840   0.04017  -0.0459   0.0131   1.0000
  11.750   1.2631   0.05119   0.04320  -0.0449   0.0125   1.0000
  12.000   1.2605   0.05423   0.04645  -0.0441   0.0118   1.0000
  12.250   1.2562   0.05761   0.05005  -0.0436   0.0114   1.0000
  12.500   1.2511   0.06125   0.05390  -0.0434   0.0111   1.0000
  12.750   1.2455   0.06515   0.05799  -0.0435   0.0109   1.0000
  13.000   1.2393   0.06929   0.06233  -0.0439   0.0107   1.0000
  13.250   1.2330   0.07364   0.06688  -0.0446   0.0105   1.0000
  13.500   1.2264   0.07823   0.07167  -0.0457   0.0103   1.0000
  13.750   1.2195   0.08309   0.07672  -0.0470   0.0102   1.0000
  14.000   1.2119   0.08826   0.08210  -0.0487   0.0101   1.0000
  14.250   1.2037   0.09379   0.08782  -0.0508   0.0100   1.0000
  14.500   1.1949   0.09964   0.09388  -0.0533   0.0099   1.0000
  14.750   1.1854   0.10590   0.10035  -0.0563   0.0099   1.0000
  15.000   1.1748   0.11264   0.10729  -0.0598   0.0099   1.0000
  15.250   1.1638   0.11977   0.11461  -0.0637   0.0099   1.0000
  15.500   1.1520   0.12737   0.12241  -0.0680   0.0099   1.0000
  15.750   1.1393   0.13552   0.13074  -0.0729   0.0100   1.0000
  16.000   1.1261   0.14424   0.13963  -0.0782   0.0101   1.0000
  16.250   1.1120   0.15362   0.14916  -0.0840   0.0103   1.0000
  16.500   1.0975   0.16367   0.15933  -0.0901   0.0105   1.0000
  16.750   1.0818   0.17483   0.17060  -0.0967   0.0108   1.0000
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