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HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il)
Reynolds number: 500,000
Max Cl/Cd: 113.54 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq17-il-500000.txt
Download as CSV file: xf-hq17-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURE
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0089   0.08623   0.08339  -0.1244   0.8626   0.0193
 -11.250  -0.0370   0.08840   0.08543  -0.1390   0.8773   0.0193
 -11.000  -0.0472   0.08252   0.07956  -0.1406   0.8742   0.0198
 -10.750  -0.0401   0.08075   0.07778  -0.1405   0.8711   0.0204
 -10.500  -0.0399   0.07740   0.07444  -0.1416   0.8674   0.0205
 -10.250  -0.0323   0.07572   0.07274  -0.1419   0.8640   0.0214
 -10.000  -0.0308   0.07268   0.06968  -0.1432   0.8607   0.0219
  -9.750  -0.0364   0.06852   0.06555  -0.1449   0.8569   0.0218
  -9.500  -0.0381   0.06523   0.06227  -0.1465   0.8528   0.0237
  -9.250  -0.0572   0.05885   0.05588  -0.1509   0.8483   0.0224
  -9.000  -0.0783   0.05422   0.05121  -0.1524   0.8437   0.0224
  -8.750  -0.0989   0.05101   0.04795  -0.1509   0.8384   0.0225
  -8.500  -0.1157   0.04840   0.04523  -0.1485   0.8342   0.0230
  -8.250  -0.1234   0.04531   0.04199  -0.1467   0.8305   0.0244
  -7.500  -0.1447   0.03397   0.02966  -0.1388   0.8191   0.0276
  -7.250  -0.1291   0.03230   0.02798  -0.1382   0.8166   0.0285
  -7.000  -0.1138   0.03095   0.02657  -0.1374   0.8136   0.0296
  -6.750  -0.0982   0.02934   0.02479  -0.1363   0.8107   0.0314
  -6.500  -0.0701   0.03120   0.02634  -0.1354   0.8083   0.0357
  -6.250  -0.0708   0.02196   0.01619  -0.1318   0.8059   0.0275
  -6.000  -0.0454   0.02113   0.01515  -0.1314   0.8040   0.0269
  -5.750  -0.0222   0.02009   0.01397  -0.1308   0.8012   0.0266
  -5.500   0.0013   0.01853   0.01224  -0.1302   0.7984   0.0267
  -5.250   0.0250   0.01644   0.00999  -0.1298   0.7959   0.0277
  -5.000   0.0507   0.01540   0.00887  -0.1296   0.7937   0.0283
  -4.750   0.0767   0.01462   0.00801  -0.1294   0.7918   0.0287
  -4.500   0.1028   0.01403   0.00736  -0.1293   0.7900   0.0294
  -4.250   0.1262   0.01354   0.00687  -0.1288   0.7873   0.0301
  -4.000   0.1505   0.01313   0.00645  -0.1284   0.7846   0.0313
  -3.750   0.1757   0.01277   0.00605  -0.1281   0.7821   0.0329
  -3.500   0.2015   0.01238   0.00561  -0.1280   0.7799   0.0340
  -3.250   0.2283   0.01205   0.00522  -0.1280   0.7780   0.0352
  -3.000   0.2552   0.01169   0.00478  -0.1281   0.7762   0.0370
  -2.750   0.2792   0.01141   0.00451  -0.1276   0.7732   0.0410
  -2.500   0.3051   0.01122   0.00430  -0.1275   0.7704   0.0475
  -2.250   0.3265   0.01026   0.00404  -0.1271   0.7679   0.2320
  -2.000   0.3423   0.00871   0.00379  -0.1261   0.7656   0.6183
  -1.750   0.3661   0.00863   0.00406  -0.1250   0.7636   0.7408
  -1.500   0.3928   0.00881   0.00422  -0.1246   0.7609   0.7722
  -1.250   0.4173   0.00909   0.00453  -0.1237   0.7576   0.7906
  -1.000   0.4425   0.00945   0.00487  -0.1228   0.7547   0.8064
  -0.750   0.4689   0.00971   0.00510  -0.1222   0.7522   0.8174
  -0.500   0.4962   0.00997   0.00530  -0.1218   0.7498   0.8285
  -0.250   0.5210   0.01012   0.00544  -0.1210   0.7470   0.8326
   0.000   0.5444   0.01024   0.00557  -0.1201   0.7433   0.8388
   0.250   0.5686   0.01035   0.00567  -0.1192   0.7401   0.8461
   0.500   0.5948   0.01040   0.00569  -0.1188   0.7374   0.8513
   0.750   0.6250   0.01041   0.00563  -0.1196   0.7350   0.8551
   1.000   0.6508   0.01043   0.00564  -0.1195   0.7317   0.8579
   1.250   0.6753   0.01039   0.00562  -0.1191   0.7281   0.8601
   1.500   0.7023   0.01036   0.00558  -0.1191   0.7250   0.8625
   1.750   0.7313   0.01034   0.00552  -0.1196   0.7224   0.8651
   2.000   0.7598   0.01037   0.00552  -0.1201   0.7196   0.8679
   2.250   0.7858   0.01042   0.00560  -0.1201   0.7158   0.8707
   2.500   0.8111   0.01035   0.00554  -0.1198   0.7123   0.8728
   2.750   0.8389   0.01030   0.00547  -0.1200   0.7090   0.8750
   3.000   0.8663   0.01031   0.00547  -0.1202   0.7052   0.8772
   3.250   0.8896   0.01030   0.00550  -0.1196   0.6998   0.8796
   3.500   0.9178   0.01025   0.00542  -0.1199   0.6944   0.8818
   3.750   0.9437   0.01028   0.00546  -0.1199   0.6890   0.8839
   4.000   0.9666   0.01020   0.00541  -0.1192   0.6832   0.8856
   4.250   0.9939   0.01014   0.00533  -0.1193   0.6780   0.8872
   4.500   1.0140   0.01013   0.00539  -0.1180   0.6716   0.8895
   4.750   1.0393   0.01012   0.00539  -0.1178   0.6666   0.8918
   5.000   1.0645   0.01017   0.00547  -0.1176   0.6618   0.8942
   5.250   1.0866   0.01021   0.00556  -0.1168   0.6553   0.8963
   5.500   1.1087   0.01022   0.00557  -0.1159   0.6466   0.8977
   5.750   1.1265   0.01019   0.00558  -0.1142   0.6374   0.8997
   6.000   1.1414   0.01020   0.00565  -0.1118   0.6264   0.9020
   6.250   1.1586   0.01025   0.00572  -0.1100   0.6178   0.9040
   6.500   1.1717   0.01032   0.00577  -0.1073   0.6069   0.9061
   6.750   1.1825   0.01052   0.00593  -0.1042   0.5930   0.9084
   7.000   1.1893   0.01084   0.00623  -0.1005   0.5749   0.9109
   7.250   1.1959   0.01113   0.00653  -0.0968   0.5562   0.9136
   7.500   1.1958   0.01164   0.00697  -0.0920   0.5281   0.9165
   7.750   1.1928   0.01238   0.00759  -0.0870   0.4979   0.9198
   8.000   1.1834   0.01349   0.00850  -0.0812   0.4610   0.9236
   8.250   1.1728   0.01485   0.00965  -0.0756   0.4134   0.9273
   8.500   1.1649   0.01627   0.01088  -0.0708   0.3759   0.9314
   8.750   1.1630   0.01760   0.01207  -0.0671   0.3426   0.9359
   9.000   1.1659   0.01887   0.01323  -0.0643   0.3133   0.9400
   9.250   1.1670   0.02052   0.01468  -0.0619   0.2689   0.9456
   9.500   1.1742   0.02225   0.01625  -0.0608   0.2332   0.9524
   9.750   1.1859   0.02389   0.01773  -0.0607   0.1936   0.9722
  10.000   1.1814   0.02575   0.01934  -0.0574   0.1514   1.0000
  10.250   1.1882   0.02719   0.02067  -0.0558   0.1293   1.0000
  10.500   1.1866   0.02925   0.02246  -0.0534   0.0879   1.0000
  10.750   1.1941   0.03074   0.02387  -0.0520   0.0714   1.0000
  11.000   1.2011   0.03228   0.02534  -0.0506   0.0558   1.0000
  11.250   1.2109   0.03368   0.02671  -0.0495   0.0440   1.0000
  11.500   1.2100   0.03593   0.02877  -0.0476   0.0195   1.0000
  11.750   1.2175   0.03758   0.03043  -0.0464   0.0130   1.0000
  12.000   1.2256   0.03923   0.03211  -0.0453   0.0097   1.0000
  12.250   1.2355   0.04074   0.03366  -0.0444   0.0086   1.0000
  12.500   1.2444   0.04238   0.03536  -0.0436   0.0078   1.0000
  12.750   1.2525   0.04412   0.03718  -0.0426   0.0074   1.0000
  13.000   1.2613   0.04581   0.03896  -0.0419   0.0072   1.0000
  13.250   1.2692   0.04763   0.04086  -0.0411   0.0069   1.0000
  13.500   1.2758   0.04962   0.04295  -0.0403   0.0066   1.0000
  13.750   1.2815   0.05172   0.04514  -0.0396   0.0065   1.0000
  14.000   1.2857   0.05400   0.04752  -0.0389   0.0062   1.0000
  14.250   1.2894   0.05640   0.05000  -0.0382   0.0061   1.0000
  14.500   1.2923   0.05894   0.05264  -0.0376   0.0060   1.0000
  14.750   1.2956   0.06150   0.05530  -0.0371   0.0061   1.0000
  15.000   1.2938   0.06467   0.05856  -0.0366   0.0057   1.0000
  15.250   1.2964   0.06740   0.06139  -0.0363   0.0058   1.0000
  15.500   1.2937   0.07082   0.06491  -0.0360   0.0056   1.0000
  15.750   1.2938   0.07397   0.06816  -0.0359   0.0056   1.0000
  16.000   1.2919   0.07742   0.07172  -0.0357   0.0055   1.0000
  16.250   1.2929   0.08053   0.07493  -0.0358   0.0055   1.0000
  16.500   1.2934   0.08376   0.07828  -0.0359   0.0055   1.0000
  16.750   1.2925   0.08719   0.08181  -0.0360   0.0055   1.0000
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