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HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il)
Reynolds number: 100,000
Max Cl/Cd: 45.13 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1010-il-100000-n5.txt
Download as CSV file: xf-hq1010-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/10 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5861   0.08911   0.08422  -0.0201   1.0000   0.0211
 -10.000  -0.5984   0.08088   0.07606  -0.0253   1.0000   0.0208
  -9.750  -0.6252   0.06882   0.06403  -0.0347   1.0000   0.0198
  -9.500  -0.6564   0.06097   0.05604  -0.0402   1.0000   0.0193
  -9.250  -0.6800   0.05611   0.05100  -0.0407   1.0000   0.0190
  -9.000  -0.6929   0.05169   0.04632  -0.0405   1.0000   0.0190
  -8.750  -0.6986   0.04757   0.04189  -0.0398   1.0000   0.0191
  -8.500  -0.6985   0.04380   0.03776  -0.0388   1.0000   0.0193
  -8.250  -0.6933   0.04043   0.03402  -0.0376   1.0000   0.0197
  -8.000  -0.6845   0.03726   0.03046  -0.0363   1.0000   0.0203
  -7.750  -0.6719   0.03476   0.02756  -0.0351   1.0000   0.0216
  -7.500  -0.6570   0.03248   0.02487  -0.0337   1.0000   0.0237
  -7.250  -0.6402   0.03025   0.02215  -0.0322   1.0000   0.0255
  -7.000  -0.6238   0.02761   0.01927  -0.0308   1.0000   0.0268
  -6.750  -0.6060   0.02594   0.01749  -0.0295   1.0000   0.0287
  -6.500  -0.5874   0.02455   0.01597  -0.0281   1.0000   0.0314
  -6.250  -0.5680   0.02347   0.01462  -0.0266   1.0000   0.0360
  -6.000  -0.5511   0.02214   0.01332  -0.0252   1.0000   0.0406
  -5.750  -0.5332   0.02115   0.01221  -0.0235   1.0000   0.0465
  -5.500  -0.5165   0.02022   0.01124  -0.0219   1.0000   0.0540
  -5.250  -0.4995   0.01943   0.01034  -0.0202   1.0000   0.0620
  -5.000  -0.4830   0.01873   0.00964  -0.0186   1.0000   0.0725
  -4.750  -0.4664   0.01806   0.00897  -0.0170   1.0000   0.0837
  -4.500  -0.4327   0.01725   0.00815  -0.0187   0.9930   0.1023
  -4.250  -0.3994   0.01644   0.00744  -0.0205   0.9858   0.1304
  -4.000  -0.3676   0.01556   0.00686  -0.0221   0.9783   0.1980
  -3.750  -0.3350   0.01460   0.00638  -0.0239   0.9718   0.3044
  -3.500  -0.3075   0.01376   0.00620  -0.0244   0.9635   0.4527
  -3.250  -0.2741   0.01347   0.00622  -0.0254   0.9576   0.5562
  -3.000  -0.2444   0.01339   0.00620  -0.0255   0.9490   0.6196
  -2.750  -0.2114   0.01340   0.00623  -0.0261   0.9428   0.6673
  -2.500  -0.1827   0.01342   0.00624  -0.0258   0.9340   0.7031
  -2.250  -0.1512   0.01343   0.00620  -0.0261   0.9268   0.7293
  -2.000  -0.1205   0.01342   0.00609  -0.0264   0.9189   0.7485
  -1.750  -0.0899   0.01340   0.00602  -0.0266   0.9112   0.7654
  -1.500  -0.0595   0.01339   0.00597  -0.0267   0.9037   0.7853
  -1.250  -0.0318   0.01339   0.00592  -0.0263   0.8951   0.8051
  -1.000  -0.0006   0.01334   0.00584  -0.0265   0.8881   0.8209
  -0.750   0.0270   0.01331   0.00578  -0.0263   0.8785   0.8339
  -0.500   0.0566   0.01327   0.00569  -0.0264   0.8703   0.8460
  -0.250   0.0861   0.01322   0.00561  -0.0264   0.8617   0.8577
   0.000   0.1147   0.01319   0.00558  -0.0263   0.8523   0.8696
   0.250   0.1457   0.01315   0.00553  -0.0267   0.8445   0.8816
   0.500   0.1756   0.01313   0.00553  -0.0269   0.8348   0.8943
   0.750   0.2073   0.01311   0.00551  -0.0274   0.8246   0.9070
   1.000   0.2406   0.01305   0.00546  -0.0282   0.8122   0.9197
   1.250   0.2746   0.01297   0.00539  -0.0291   0.7969   0.9327
   1.500   0.3095   0.01288   0.00530  -0.0301   0.7803   0.9462
   1.750   0.3459   0.01282   0.00525  -0.0317   0.7652   0.9600
   2.000   0.3832   0.01279   0.00525  -0.0336   0.7512   0.9741
   2.250   0.4210   0.01276   0.00528  -0.0356   0.7364   0.9888
   2.500   0.4514   0.01277   0.00530  -0.0363   0.7209   1.0000
   2.750   0.4717   0.01282   0.00534  -0.0349   0.7049   1.0000
   3.000   0.4929   0.01290   0.00546  -0.0336   0.6862   1.0000
   3.250   0.5153   0.01298   0.00554  -0.0324   0.6659   1.0000
   3.500   0.5381   0.01307   0.00564  -0.0313   0.6418   1.0000
   3.750   0.5610   0.01319   0.00573  -0.0301   0.6127   1.0000
   4.000   0.5838   0.01334   0.00582  -0.0289   0.5773   1.0000
   4.250   0.6063   0.01356   0.00598  -0.0276   0.5330   1.0000
   4.500   0.6278   0.01391   0.00613  -0.0263   0.4784   1.0000
   4.750   0.6483   0.01442   0.00637  -0.0249   0.4170   1.0000
   5.000   0.6686   0.01504   0.00674  -0.0236   0.3594   1.0000
   5.250   0.6890   0.01572   0.00720  -0.0226   0.3123   1.0000
   5.500   0.7100   0.01639   0.00777  -0.0216   0.2747   1.0000
   5.750   0.7312   0.01708   0.00835  -0.0207   0.2404   1.0000
   6.000   0.7527   0.01774   0.00896  -0.0199   0.2063   1.0000
   6.250   0.7738   0.01846   0.00959  -0.0190   0.1722   1.0000
   6.500   0.7945   0.01926   0.01030  -0.0181   0.1411   1.0000
   6.750   0.8143   0.02018   0.01110  -0.0172   0.1151   1.0000
   7.000   0.8340   0.02114   0.01207  -0.0162   0.0956   1.0000
   7.250   0.8528   0.02220   0.01307  -0.0151   0.0799   1.0000
   7.500   0.8717   0.02327   0.01418  -0.0140   0.0675   1.0000
   7.750   0.8905   0.02435   0.01534  -0.0129   0.0564   1.0000
   8.000   0.9076   0.02572   0.01683  -0.0115   0.0489   1.0000
   8.250   0.9237   0.02710   0.01822  -0.0103   0.0412   1.0000
   8.500   0.9416   0.02824   0.01952  -0.0092   0.0340   1.0000
   8.750   0.9562   0.02988   0.02128  -0.0077   0.0293   1.0000
   9.000   0.9717   0.03144   0.02308  -0.0063   0.0252   1.0000
   9.250   0.9837   0.03311   0.02481  -0.0050   0.0224   1.0000
   9.500   0.9967   0.03514   0.02711  -0.0034   0.0199   1.0000
   9.750   1.0085   0.03743   0.02968  -0.0018   0.0187   1.0000
  10.000   1.0178   0.03982   0.03235  -0.0002   0.0177   1.0000
  10.250   1.0233   0.04230   0.03509   0.0017   0.0170   1.0000
  10.500   1.0242   0.04479   0.03782   0.0038   0.0164   1.0000
  10.750   1.0219   0.04746   0.04074   0.0059   0.0160   1.0000
  11.000   1.0166   0.05035   0.04386   0.0075   0.0157   1.0000
  11.250   1.0079   0.05369   0.04743   0.0085   0.0155   1.0000
  11.500   0.9970   0.05739   0.05136   0.0088   0.0153   1.0000
  11.750   0.9833   0.06166   0.05587   0.0082   0.0153   1.0000
  12.000   0.9674   0.06661   0.06104   0.0066   0.0152   1.0000
  12.250   0.9482   0.07266   0.06735   0.0036   0.0154   1.0000
  12.500   0.9243   0.08042   0.07535  -0.0013   0.0156   1.0000
  12.750   0.8936   0.09113   0.08630  -0.0088   0.0160   1.0000
  13.000   0.8440   0.10975   0.10510  -0.0213   0.0174   1.0000
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