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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 100,000
Max Cl/Cd: 57.45 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3011-il-100000-n5.txt
Download as CSV file: xf-hq3011-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/11 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3709   0.09141   0.08655  -0.0442   1.0000   0.0242
  -9.000  -0.3772   0.08746   0.08268  -0.0451   1.0000   0.0239
  -8.750  -0.3859   0.08361   0.07893  -0.0458   1.0000   0.0234
  -8.500  -0.3995   0.07983   0.07528  -0.0461   1.0000   0.0230
  -8.250  -0.4209   0.07638   0.07196  -0.0454   1.0000   0.0226
  -8.000  -0.4512   0.07313   0.06883  -0.0440   1.0000   0.0222
  -7.500  -0.4576   0.05356   0.04866  -0.0630   0.9835   0.0207
  -7.250  -0.4450   0.04812   0.04287  -0.0672   0.9752   0.0210
  -7.000  -0.4226   0.04547   0.04006  -0.0702   0.9697   0.0222
  -6.750  -0.4012   0.04273   0.03707  -0.0723   0.9628   0.0237
  -6.500  -0.3752   0.03828   0.03207  -0.0755   0.9581   0.0248
  -6.250  -0.3544   0.03436   0.02758  -0.0764   0.9508   0.0253
  -6.000  -0.3257   0.03078   0.02338  -0.0779   0.9463   0.0260
  -5.750  -0.2925   0.02778   0.01978  -0.0796   0.9434   0.0274
  -5.500  -0.2680   0.02584   0.01741  -0.0792   0.9365   0.0287
  -5.250  -0.2369   0.02424   0.01568  -0.0805   0.9326   0.0317
  -5.000  -0.2021   0.02312   0.01434  -0.0820   0.9296   0.0372
  -4.750  -0.1777   0.02186   0.01298  -0.0815   0.9229   0.0416
  -4.500  -0.1457   0.02110   0.01206  -0.0824   0.9186   0.0515
  -4.250  -0.1119   0.02029   0.01122  -0.0839   0.9155   0.0645
  -4.000  -0.0883   0.01966   0.01059  -0.0834   0.9082   0.0753
  -3.750  -0.0572   0.01895   0.00984  -0.0841   0.9039   0.0861
  -3.500  -0.0273   0.01836   0.00920  -0.0847   0.8992   0.0998
  -3.250  -0.0012   0.01785   0.00869  -0.0845   0.8926   0.1167
  -3.000   0.0303   0.01713   0.00815  -0.0856   0.8886   0.1634
  -2.750   0.0529   0.01604   0.00781  -0.0854   0.8819   0.3339
  -2.250   0.1076   0.01542   0.00791  -0.0846   0.8721   0.6080
  -2.000   0.1297   0.01544   0.00793  -0.0832   0.8643   0.6483
  -1.750   0.1572   0.01535   0.00790  -0.0824   0.8597   0.6973
  -1.500   0.1762   0.01537   0.00804  -0.0799   0.8520   0.7413
  -1.250   0.2013   0.01533   0.00801  -0.0785   0.8465   0.7740
  -1.000   0.2259   0.01532   0.00795  -0.0775   0.8395   0.7919
  -0.750   0.2538   0.01525   0.00781  -0.0772   0.8331   0.8060
  -0.500   0.2812   0.01519   0.00768  -0.0769   0.8266   0.8206
  -0.250   0.3078   0.01513   0.00756  -0.0764   0.8193   0.8369
   0.000   0.3356   0.01504   0.00743  -0.0762   0.8128   0.8551
   0.250   0.3619   0.01496   0.00733  -0.0757   0.8051   0.8749
   0.500   0.3916   0.01483   0.00719  -0.0757   0.7987   0.8964
   0.750   0.4253   0.01474   0.00709  -0.0767   0.7912   0.9209
   1.000   0.4670   0.01461   0.00695  -0.0794   0.7847   0.9542
   1.250   0.5048   0.01448   0.00676  -0.0814   0.7750   1.0000
   1.500   0.5310   0.01446   0.00667  -0.0811   0.7632   1.0000
   1.750   0.5581   0.01444   0.00658  -0.0809   0.7518   1.0000
   2.000   0.5865   0.01442   0.00652  -0.0809   0.7419   1.0000
   2.250   0.6141   0.01445   0.00651  -0.0808   0.7315   1.0000
   2.500   0.6400   0.01453   0.00657  -0.0804   0.7197   1.0000
   2.750   0.6666   0.01459   0.00661  -0.0800   0.7075   1.0000
   3.000   0.6932   0.01464   0.00667  -0.0797   0.6945   1.0000
   3.250   0.7197   0.01469   0.00671  -0.0792   0.6800   1.0000
   3.500   0.7459   0.01475   0.00675  -0.0787   0.6640   1.0000
   3.750   0.7720   0.01482   0.00682  -0.0782   0.6468   1.0000
   4.000   0.7975   0.01493   0.00692  -0.0776   0.6283   1.0000
   4.250   0.8220   0.01507   0.00707  -0.0768   0.6077   1.0000
   4.500   0.8469   0.01522   0.00719  -0.0761   0.5858   1.0000
   4.750   0.8711   0.01541   0.00738  -0.0753   0.5607   1.0000
   5.000   0.8946   0.01566   0.00757  -0.0743   0.5329   1.0000
   5.250   0.9174   0.01597   0.00779  -0.0733   0.5026   1.0000
   5.500   0.9392   0.01636   0.00808  -0.0722   0.4708   1.0000
   5.750   0.9603   0.01683   0.00846  -0.0710   0.4389   1.0000
   6.000   0.9807   0.01736   0.00888  -0.0698   0.4083   1.0000
   6.250   1.0004   0.01793   0.00937  -0.0685   0.3790   1.0000
   6.500   1.0199   0.01854   0.00990  -0.0672   0.3517   1.0000
   6.750   1.0387   0.01919   0.01047  -0.0659   0.3262   1.0000
   7.000   1.0571   0.01987   0.01112  -0.0646   0.3033   1.0000
   7.250   1.0755   0.02056   0.01178  -0.0632   0.2818   1.0000
   7.500   1.0931   0.02130   0.01247  -0.0618   0.2615   1.0000
   7.750   1.1104   0.02203   0.01320  -0.0604   0.2419   1.0000
   8.000   1.1274   0.02276   0.01395  -0.0590   0.2228   1.0000
   8.250   1.1432   0.02355   0.01473  -0.0575   0.2049   1.0000
   8.500   1.1580   0.02437   0.01558  -0.0558   0.1881   1.0000
   8.750   1.1721   0.02518   0.01643  -0.0540   0.1723   1.0000
   9.000   1.1850   0.02605   0.01734  -0.0521   0.1575   1.0000
   9.250   1.1971   0.02700   0.01832  -0.0502   0.1431   1.0000
   9.500   1.2084   0.02801   0.01937  -0.0483   0.1278   1.0000
   9.750   1.2185   0.02911   0.02047  -0.0464   0.1122   1.0000
  10.000   1.2280   0.03030   0.02167  -0.0445   0.0985   1.0000
  10.250   1.2373   0.03157   0.02300  -0.0428   0.0880   1.0000
  10.500   1.2449   0.03298   0.02449  -0.0409   0.0795   1.0000
  10.750   1.2519   0.03447   0.02602  -0.0393   0.0700   1.0000
  11.000   1.2598   0.03596   0.02758  -0.0378   0.0601   1.0000
  11.250   1.2660   0.03762   0.02933  -0.0363   0.0522   1.0000
  11.500   1.2693   0.03956   0.03133  -0.0349   0.0467   1.0000
  11.750   1.2745   0.04142   0.03335  -0.0336   0.0402   1.0000
  12.000   1.2754   0.04374   0.03571  -0.0324   0.0339   1.0000
  12.250   1.2762   0.04616   0.03830  -0.0313   0.0288   1.0000
  12.500   1.2717   0.04921   0.04143  -0.0304   0.0255   1.0000
  12.750   1.2687   0.05226   0.04470  -0.0297   0.0226   1.0000
  13.000   1.2625   0.05581   0.04840  -0.0294   0.0203   1.0000
  13.250   1.2537   0.05981   0.05253  -0.0296   0.0191   1.0000
  13.500   1.2438   0.06418   0.05707  -0.0300   0.0181   1.0000
  13.750   1.2346   0.06872   0.06183  -0.0309   0.0172   1.0000
  14.000   1.2251   0.07355   0.06686  -0.0321   0.0165   1.0000
  14.250   1.2146   0.07881   0.07232  -0.0338   0.0159   1.0000
  14.500   1.2041   0.08434   0.07804  -0.0359   0.0156   1.0000
  14.750   1.1929   0.09027   0.08420  -0.0385   0.0152   1.0000
  15.000   1.1810   0.09661   0.09072  -0.0414   0.0148   1.0000
  15.250   1.1689   0.10325   0.09753  -0.0447   0.0145   1.0000
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