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HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il)
Reynolds number: 500,000
Max Cl/Cd: 107.55 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq300gd2-il-500000.txt
Download as CSV file: xf-hq300gd2-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HORSTMANN AND QUAST HQ-300 GD(MOD 2) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3843   0.05527   0.05180  -0.0926   0.7853   0.0270
  -9.250  -0.4373   0.04045   0.03625  -0.0937   0.7799   0.0223
  -9.000  -0.4187   0.03873   0.03452  -0.0937   0.7740   0.0208
  -8.750  -0.4143   0.03381   0.02918  -0.0936   0.7680   0.0206
  -8.500  -0.4037   0.02933   0.02415  -0.0933   0.7628   0.0208
  -8.250  -0.3862   0.02595   0.02029  -0.0931   0.7577   0.0211
  -8.000  -0.3634   0.02392   0.01790  -0.0931   0.7524   0.0215
  -7.750  -0.3406   0.02165   0.01525  -0.0930   0.7478   0.0221
  -7.500  -0.3159   0.02017   0.01366  -0.0931   0.7432   0.0229
  -7.250  -0.2891   0.01951   0.01296  -0.0935   0.7380   0.0237
  -7.000  -0.2619   0.01895   0.01232  -0.0938   0.7332   0.0249
  -6.750  -0.2347   0.01829   0.01148  -0.0939   0.7290   0.0260
  -6.500  -0.2068   0.01764   0.01071  -0.0941   0.7246   0.0268
  -6.250  -0.1813   0.01634   0.00932  -0.0939   0.7203   0.0278
  -6.000  -0.1547   0.01560   0.00856  -0.0941   0.7163   0.0289
  -5.750  -0.1268   0.01523   0.00813  -0.0944   0.7123   0.0303
  -5.500  -0.0985   0.01481   0.00769  -0.0948   0.7081   0.0318
  -5.250  -0.0702   0.01439   0.00722  -0.0951   0.7040   0.0330
  -5.000  -0.0422   0.01379   0.00655  -0.0955   0.7003   0.0341
  -4.750  -0.0136   0.01324   0.00596  -0.0961   0.6968   0.0361
  -4.500   0.0160   0.01292   0.00565  -0.0969   0.6931   0.0383
  -4.250   0.0459   0.01261   0.00530  -0.0976   0.6892   0.0403
  -4.000   0.0763   0.01219   0.00485  -0.0985   0.6855   0.0428
  -3.750   0.1068   0.01191   0.00454  -0.0994   0.6823   0.0470
  -3.500   0.1378   0.01165   0.00425  -0.1004   0.6791   0.0536
  -3.250   0.1693   0.01129   0.00397  -0.1015   0.6756   0.0713
  -3.000   0.2088   0.00978   0.00352  -0.1060   0.6720   0.3444
  -2.750   0.2534   0.00860   0.00335  -0.1111   0.6687   0.6261
  -2.500   0.2834   0.00868   0.00357  -0.1114   0.6656   0.6976
  -2.250   0.3127   0.00885   0.00375  -0.1116   0.6625   0.7253
  -2.000   0.3425   0.00904   0.00391  -0.1119   0.6590   0.7438
  -1.750   0.3696   0.00935   0.00421  -0.1114   0.6556   0.7599
  -1.500   0.3928   0.00971   0.00458  -0.1098   0.6525   0.7691
  -1.250   0.4201   0.01000   0.00480  -0.1095   0.6495   0.7781
  -1.000   0.4447   0.01024   0.00506  -0.1085   0.6464   0.7828
  -0.750   0.4735   0.01035   0.00515  -0.1087   0.6430   0.7874
  -0.500   0.5060   0.01040   0.00513  -0.1099   0.6396   0.7923
  -0.250   0.5326   0.01050   0.00520  -0.1096   0.6365   0.7945
   0.000   0.5593   0.01067   0.00532  -0.1093   0.6335   0.7970
   0.250   0.5867   0.01079   0.00544  -0.1091   0.6303   0.8003
   0.500   0.6158   0.01088   0.00553  -0.1095   0.6266   0.8049
   0.750   0.6457   0.01095   0.00557  -0.1101   0.6228   0.8093
   1.000   0.6713   0.01105   0.00564  -0.1095   0.6193   0.8116
   1.250   0.6984   0.01116   0.00574  -0.1094   0.6155   0.8139
   1.500   0.7266   0.01120   0.00580  -0.1096   0.6114   0.8162
   1.750   0.7562   0.01123   0.00581  -0.1101   0.6073   0.8189
   2.000   0.7878   0.01127   0.00581  -0.1112   0.6035   0.8219
   2.250   0.8199   0.01133   0.00584  -0.1125   0.5997   0.8246
   2.500   0.8472   0.01133   0.00588  -0.1125   0.5956   0.8260
   2.750   0.8747   0.01137   0.00593  -0.1126   0.5914   0.8275
   3.000   0.9027   0.01144   0.00597  -0.1128   0.5877   0.8293
   3.250   0.9311   0.01151   0.00606  -0.1131   0.5836   0.8310
   3.500   0.9599   0.01154   0.00614  -0.1136   0.5791   0.8330
   3.750   0.9896   0.01158   0.00618  -0.1142   0.5747   0.8354
   4.000   1.0206   0.01168   0.00623  -0.1153   0.5704   0.8377
   4.250   1.0525   0.01171   0.00632  -0.1166   0.5653   0.8398
   4.500   1.0793   0.01171   0.00636  -0.1165   0.5601   0.8412
   4.750   1.1062   0.01180   0.00642  -0.1165   0.5551   0.8427
   5.000   1.1333   0.01183   0.00654  -0.1166   0.5493   0.8442
   5.250   1.1608   0.01188   0.00662  -0.1168   0.5432   0.8458
   5.500   1.1885   0.01197   0.00672  -0.1171   0.5371   0.8475
   5.750   1.2163   0.01203   0.00684  -0.1174   0.5298   0.8495
   6.000   1.2445   0.01215   0.00695  -0.1179   0.5226   0.8517
   6.250   1.2735   0.01223   0.00709  -0.1185   0.5139   0.8536
   6.500   1.3023   0.01236   0.00723  -0.1192   0.5053   0.8553
   6.750   1.3272   0.01247   0.00736  -0.1189   0.4953   0.8566
   7.000   1.3517   0.01260   0.00754  -0.1186   0.4846   0.8582
   7.250   1.3756   0.01279   0.00774  -0.1182   0.4727   0.8599
   7.500   1.3992   0.01303   0.00799  -0.1177   0.4591   0.8617
   7.750   1.4222   0.01331   0.00826  -0.1173   0.4436   0.8634
   8.000   1.4444   0.01367   0.00859  -0.1168   0.4262   0.8653
   8.250   1.4653   0.01410   0.00899  -0.1161   0.4078   0.8672
   8.500   1.4845   0.01466   0.00948  -0.1152   0.3885   0.8694
   8.750   1.4999   0.01522   0.00999  -0.1135   0.3694   0.8712
   9.000   1.5103   0.01589   0.01060  -0.1110   0.3476   0.8730
   9.250   1.5123   0.01675   0.01136  -0.1071   0.3266   0.8752
   9.500   1.5204   0.01772   0.01227  -0.1047   0.3050   0.8773
   9.750   1.5294   0.01876   0.01327  -0.1027   0.2872   0.8795
  10.000   1.5397   0.01984   0.01432  -0.1011   0.2727   0.8819
  10.250   1.5500   0.02103   0.01550  -0.0997   0.2587   0.8841
  10.500   1.5579   0.02231   0.01676  -0.0980   0.2452   0.8859
  10.750   1.5643   0.02373   0.01818  -0.0963   0.2315   0.8876
  11.000   1.5699   0.02531   0.01974  -0.0947   0.2179   0.8895
  11.250   1.5750   0.02702   0.02144  -0.0932   0.2040   0.8914
  11.500   1.5792   0.02887   0.02327  -0.0918   0.1904   0.8934
  11.750   1.5824   0.03088   0.02526  -0.0905   0.1768   0.8956
  12.000   1.5849   0.03302   0.02737  -0.0892   0.1633   0.8977
  12.250   1.5864   0.03523   0.02955  -0.0879   0.1501   0.8993
  12.500   1.5862   0.03752   0.03183  -0.0865   0.1372   0.9009
  12.750   1.5851   0.03995   0.03424  -0.0851   0.1246   0.9026
  13.000   1.5835   0.04251   0.03679  -0.0838   0.1122   0.9043
  13.250   1.5811   0.04526   0.03952  -0.0826   0.0996   0.9060
  13.500   1.5776   0.04820   0.04241  -0.0816   0.0870   0.9078
  13.750   1.5726   0.05139   0.04555  -0.0806   0.0742   0.9097
  14.000   1.5676   0.05468   0.04881  -0.0798   0.0618   0.9114
  14.250   1.5611   0.05815   0.05225  -0.0790   0.0505   0.9130
  14.500   1.5541   0.06169   0.05578  -0.0782   0.0417   0.9144
  14.750   1.5477   0.06529   0.05939  -0.0776   0.0354   0.9160
  15.000   1.5404   0.06909   0.06321  -0.0771   0.0308   0.9175
  15.250   1.5377   0.07242   0.06661  -0.0768   0.0277   0.9191
  15.500   1.5303   0.07643   0.07066  -0.0766   0.0253   0.9207
  15.750   1.5293   0.07974   0.07408  -0.0767   0.0236   0.9224
  16.000   1.5253   0.08350   0.07792  -0.0768   0.0221   0.9240
  16.250   1.5175   0.08782   0.08230  -0.0771   0.0209   0.9254
  16.500   1.5113   0.09184   0.08644  -0.0773   0.0200   0.9271
  16.750   1.5082   0.09551   0.09022  -0.0776   0.0191   0.9291
  17.000   1.5036   0.09947   0.09428  -0.0781   0.0184   0.9311
  17.250   1.4978   0.10369   0.09859  -0.0788   0.0177   0.9330
  17.500   1.4889   0.10840   0.10339  -0.0797   0.0171   0.9347
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