Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.46 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq17-il-1000000-n5.txt
Download as CSV file: xf-hq17-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.6149   0.03827   0.03520  -0.1527   0.8319   0.0046
 -14.500  -0.6367   0.03437   0.03114  -0.1527   0.8287   0.0047
 -14.250  -0.6510   0.03162   0.02821  -0.1515   0.8256   0.0045
 -14.000  -0.6549   0.02973   0.02620  -0.1501   0.8228   0.0048
 -13.750  -0.6538   0.02826   0.02464  -0.1485   0.8205   0.0050
 -13.500  -0.6560   0.02665   0.02290  -0.1465   0.8178   0.0051
 -13.250  -0.6466   0.02582   0.02203  -0.1451   0.8151   0.0053
 -13.000  -0.6447   0.02457   0.02065  -0.1429   0.8120   0.0054
 -12.750  -0.6335   0.02397   0.01997  -0.1413   0.8094   0.0058
 -12.500  -0.6329   0.02282   0.01868  -0.1384   0.8066   0.0059
 -12.250  -0.6259   0.02207   0.01783  -0.1360   0.8039   0.0061
 -12.000  -0.6135   0.02128   0.01694  -0.1344   0.8014   0.0064
 -11.750  -0.6007   0.02039   0.01590  -0.1328   0.7989   0.0066
 -11.500  -0.5845   0.01967   0.01506  -0.1317   0.7967   0.0068
 -11.250  -0.5668   0.01906   0.01434  -0.1307   0.7944   0.0071
 -11.000  -0.5459   0.01863   0.01389  -0.1302   0.7921   0.0073
 -10.750  -0.5234   0.01836   0.01360  -0.1298   0.7894   0.0076
 -10.500  -0.4998   0.01820   0.01341  -0.1295   0.7868   0.0078
 -10.250  -0.4771   0.01791   0.01308  -0.1292   0.7841   0.0081
 -10.000  -0.4546   0.01757   0.01266  -0.1287   0.7815   0.0083
  -9.750  -0.4315   0.01721   0.01226  -0.1284   0.7788   0.0087
  -9.500  -0.4093   0.01669   0.01165  -0.1280   0.7758   0.0090
  -9.250  -0.3866   0.01619   0.01106  -0.1276   0.7728   0.0093
  -9.000  -0.3631   0.01579   0.01057  -0.1273   0.7700   0.0096
  -8.750  -0.3383   0.01556   0.01027  -0.1272   0.7676   0.0099
  -8.500  -0.3149   0.01505   0.00967  -0.1269   0.7653   0.0102
  -8.250  -0.2920   0.01446   0.00901  -0.1265   0.7629   0.0105
  -8.000  -0.2669   0.01424   0.00875  -0.1264   0.7604   0.0109
  -7.750  -0.2416   0.01402   0.00849  -0.1263   0.7578   0.0112
  -7.500  -0.2161   0.01382   0.00824  -0.1263   0.7555   0.0115
  -7.250  -0.1903   0.01359   0.00798  -0.1263   0.7535   0.0120
  -7.000  -0.1649   0.01319   0.00753  -0.1262   0.7513   0.0124
  -6.750  -0.1393   0.01287   0.00714  -0.1262   0.7490   0.0129
  -6.500  -0.1137   0.01253   0.00674  -0.1261   0.7466   0.0133
  -6.250  -0.0883   0.01216   0.00631  -0.1260   0.7441   0.0136
  -6.000  -0.0628   0.01183   0.00591  -0.1258   0.7419   0.0138
  -5.750  -0.0367   0.01151   0.00556  -0.1258   0.7395   0.0140
  -5.500  -0.0106   0.01120   0.00521  -0.1258   0.7364   0.0142
  -5.250   0.0156   0.01093   0.00491  -0.1258   0.7332   0.0143
  -5.000   0.0394   0.01036   0.00426  -0.1254   0.7300   0.0148
  -4.750   0.0646   0.00996   0.00381  -0.1253   0.7273   0.0153
  -4.500   0.0908   0.00968   0.00350  -0.1252   0.7247   0.0159
  -4.250   0.1174   0.00947   0.00327  -0.1253   0.7221   0.0166
  -4.000   0.1442   0.00930   0.00307  -0.1254   0.7197   0.0173
  -3.750   0.1710   0.00913   0.00286  -0.1255   0.7174   0.0179
  -3.500   0.1979   0.00898   0.00267  -0.1255   0.7152   0.0185
  -3.250   0.2252   0.00883   0.00251  -0.1257   0.7131   0.0191
  -3.000   0.2526   0.00871   0.00236  -0.1259   0.7107   0.0197
  -2.750   0.2799   0.00861   0.00223  -0.1260   0.7083   0.0201
  -2.500   0.3072   0.00852   0.00212  -0.1262   0.7058   0.0205
  -2.250   0.3344   0.00843   0.00198  -0.1263   0.7034   0.0220
  -2.000   0.3618   0.00834   0.00189  -0.1265   0.7011   0.0258
  -1.750   0.3893   0.00821   0.00182  -0.1267   0.6979   0.0359
  -1.500   0.4154   0.00797   0.00174  -0.1267   0.6927   0.0913
  -1.250   0.4413   0.00777   0.00168  -0.1267   0.6880   0.1507
  -1.000   0.4672   0.00746   0.00163  -0.1268   0.6819   0.2346
  -0.750   0.4899   0.00683   0.00153  -0.1266   0.6755   0.4280
  -0.500   0.5129   0.00622   0.00146  -0.1262   0.6715   0.6194
  -0.250   0.5369   0.00600   0.00157  -0.1257   0.6682   0.7291
   0.000   0.5635   0.00607   0.00168  -0.1255   0.6650   0.7649
   0.250   0.5907   0.00615   0.00172  -0.1256   0.6620   0.7759
   0.500   0.6182   0.00621   0.00181  -0.1257   0.6591   0.7837
   0.750   0.6457   0.00628   0.00188  -0.1258   0.6558   0.7906
   1.000   0.6725   0.00638   0.00196  -0.1258   0.6515   0.7954
   1.250   0.6995   0.00646   0.00201  -0.1258   0.6470   0.7984
   1.500   0.7272   0.00650   0.00205  -0.1261   0.6407   0.8008
   1.750   0.7537   0.00657   0.00210  -0.1261   0.6338   0.8027
   2.000   0.7797   0.00665   0.00216  -0.1259   0.6248   0.8046
   2.250   0.8043   0.00676   0.00223  -0.1255   0.6149   0.8069
   2.500   0.8281   0.00689   0.00231  -0.1249   0.6065   0.8092
   2.750   0.8528   0.00700   0.00240  -0.1246   0.5989   0.8111
   3.000   0.8756   0.00715   0.00250  -0.1238   0.5891   0.8130
   3.250   0.8970   0.00734   0.00263  -0.1228   0.5766   0.8150
   3.500   0.9177   0.00751   0.00276  -0.1216   0.5609   0.8166
   3.750   0.9327   0.00779   0.00295  -0.1193   0.5346   0.8181
   4.000   0.9339   0.00824   0.00322  -0.1141   0.4960   0.8200
   4.250   0.9332   0.00887   0.00366  -0.1087   0.4579   0.8219
   4.500   0.9272   0.00974   0.00427  -0.1026   0.4023   0.8241
   4.750   0.9363   0.01028   0.00468  -0.0995   0.3786   0.8258
   5.000   0.9443   0.01088   0.00517  -0.0963   0.3512   0.8274
   5.250   0.9538   0.01148   0.00567  -0.0935   0.3309   0.8291
   5.500   0.9618   0.01214   0.00623  -0.0905   0.3016   0.8309
   5.750   0.9647   0.01305   0.00695  -0.0867   0.2619   0.8326
   6.000   0.9695   0.01395   0.00770  -0.0834   0.2309   0.8342
   6.250   0.9636   0.01537   0.00881  -0.0786   0.1690   0.8361
   6.500   0.9660   0.01651   0.00976  -0.0752   0.1300   0.8379
   6.750   0.9594   0.01816   0.01107  -0.0707   0.0651   0.8399
   7.000   0.9764   0.01868   0.01160  -0.0696   0.0617   0.8411
   7.250   0.9932   0.01923   0.01213  -0.0685   0.0573   0.8422
   7.500   1.0110   0.01972   0.01264  -0.0675   0.0549   0.8431
   7.750   1.0238   0.02048   0.01336  -0.0659   0.0422   0.8441
   8.000   1.0379   0.02118   0.01404  -0.0645   0.0340   0.8453
   8.250   1.0467   0.02222   0.01500  -0.0624   0.0163   0.8465
   8.500   1.0615   0.02293   0.01572  -0.0612   0.0120   0.8477
   8.750   1.0726   0.02389   0.01666  -0.0596   0.0040   0.8489
   9.000   1.0881   0.02459   0.01740  -0.0585   0.0038   0.8503
   9.250   1.1030   0.02536   0.01819  -0.0574   0.0035   0.8516
   9.500   1.1174   0.02618   0.01905  -0.0563   0.0030   0.8527
   9.750   1.1316   0.02702   0.01993  -0.0552   0.0028   0.8538
  10.000   1.1462   0.02786   0.02081  -0.0542   0.0028   0.8548
  10.250   1.1602   0.02876   0.02175  -0.0532   0.0027   0.8557
  10.500   1.1738   0.02969   0.02272  -0.0521   0.0025   0.8565
  10.750   1.1872   0.03064   0.02372  -0.0511   0.0025   0.8574
  11.000   1.1990   0.03173   0.02486  -0.0499   0.0022   0.8583
  11.250   1.2118   0.03277   0.02595  -0.0489   0.0023   0.8593
  11.500   1.2230   0.03395   0.02719  -0.0478   0.0022   0.8604
  11.750   1.2341   0.03518   0.02848  -0.0467   0.0021   0.8614
  12.000   1.2452   0.03642   0.02978  -0.0457   0.0021   0.8624
  12.250   1.2557   0.03773   0.03114  -0.0447   0.0020   0.8633
  12.500   1.2655   0.03913   0.03260  -0.0438   0.0019   0.8643
  12.750   1.2744   0.04065   0.03418  -0.0427   0.0018   0.8652
  13.000   1.2825   0.04227   0.03586  -0.0418   0.0017   0.8661
  13.250   1.2897   0.04400   0.03766  -0.0408   0.0017   0.8669
  13.500   1.3003   0.04545   0.03915  -0.0402   0.0017   0.8677
  13.750   1.2980   0.04821   0.04203  -0.0387   0.0016   0.8685
  14.000   1.3022   0.05039   0.04428  -0.0378   0.0015   0.8691
  14.250   1.3075   0.05250   0.04648  -0.0371   0.0015   0.8698
  14.500   1.3085   0.05509   0.04917  -0.0363   0.0015   0.8706
  14.750   1.3142   0.05725   0.05141  -0.0358   0.0015   0.8714
  15.000   1.3178   0.05970   0.05394  -0.0353   0.0015   0.8722
  15.250   1.3199   0.06238   0.05672  -0.0349   0.0015   0.8729
  15.500   1.3259   0.06465   0.05907  -0.0347   0.0015   0.8737
  15.750   1.3278   0.06745   0.06196  -0.0345   0.0015   0.8744
  16.000   1.3349   0.06967   0.06426  -0.0346   0.0014   0.8753
  16.250   1.3353   0.07278   0.06746  -0.0346   0.0014   0.8760
  16.500   1.3354   0.07603   0.07081  -0.0347   0.0014   0.8767
  16.750   1.3388   0.07888   0.07375  -0.0350   0.0014   0.8774
  17.000   1.3389   0.08223   0.07719  -0.0354   0.0014   0.8781
  17.250   1.3403   0.08547   0.08054  -0.0359   0.0014   0.8788
  17.500   1.3386   0.08922   0.08440  -0.0365   0.0014   0.8795
  17.750   1.3350   0.09334   0.08863  -0.0374   0.0013   0.8801
  18.000   1.3337   0.09718   0.09257  -0.0384   0.0013   0.8807
  18.250   1.3306   0.10134   0.09684  -0.0395   0.0013   0.8813
  18.500   1.3302   0.10516   0.10076  -0.0408   0.0013   0.8819
  18.750   1.3241   0.10996   0.10568  -0.0424   0.0013   0.8824
<< Back to HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il)

Polar data table (+)

Polar graphs


<< Back to HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il)