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HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 0/10 AIRFOIL (hq010-il)
Reynolds number: 100,000
Max Cl/Cd: 36.04 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq010-il-100000-n5.txt
Download as CSV file: xf-hq010-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7909   0.07517   0.07012  -0.0179   1.0000   0.0211
 -11.250  -0.8098   0.06888   0.06371  -0.0222   1.0000   0.0210
 -11.000  -0.8304   0.06326   0.05793  -0.0250   1.0000   0.0208
 -10.750  -0.8493   0.05873   0.05320  -0.0263   1.0000   0.0209
 -10.500  -0.8676   0.05487   0.04909  -0.0259   1.0000   0.0210
 -10.250  -0.8844   0.05153   0.04550  -0.0239   1.0000   0.0214
 -10.000  -0.8878   0.04869   0.04256  -0.0226   1.0000   0.0225
  -9.750  -0.8830   0.04700   0.04077  -0.0215   1.0000   0.0240
  -9.500  -0.8781   0.04484   0.03838  -0.0203   1.0000   0.0259
  -9.250  -0.8730   0.04222   0.03535  -0.0187   1.0000   0.0284
  -9.000  -0.8659   0.03904   0.03161  -0.0170   1.0000   0.0300
  -8.750  -0.8536   0.03626   0.02835  -0.0156   1.0000   0.0311
  -8.500  -0.8387   0.03392   0.02593  -0.0148   1.0000   0.0336
  -8.250  -0.8208   0.03233   0.02414  -0.0140   1.0000   0.0361
  -8.000  -0.8009   0.03027   0.02178  -0.0130   1.0000   0.0378
  -7.750  -0.7795   0.02840   0.01959  -0.0121   1.0000   0.0396
  -7.500  -0.7575   0.02680   0.01774  -0.0112   1.0000   0.0414
  -7.250  -0.7367   0.02523   0.01609  -0.0104   1.0000   0.0440
  -7.000  -0.7160   0.02416   0.01500  -0.0096   1.0000   0.0479
  -6.750  -0.6946   0.02308   0.01381  -0.0087   1.0000   0.0520
  -6.500  -0.6740   0.02193   0.01255  -0.0076   1.0000   0.0555
  -6.250  -0.6544   0.02086   0.01149  -0.0065   1.0000   0.0604
  -6.000  -0.6335   0.02002   0.01054  -0.0055   1.0000   0.0678
  -5.750  -0.6134   0.01914   0.00963  -0.0045   1.0000   0.0797
  -5.500  -0.5936   0.01824   0.00878  -0.0033   1.0000   0.0946
  -5.250  -0.5746   0.01731   0.00800  -0.0022   1.0000   0.1175
  -5.000  -0.5566   0.01635   0.00742  -0.0009   1.0000   0.1682
  -4.750  -0.5378   0.01563   0.00691   0.0003   1.0000   0.2279
  -4.500  -0.5205   0.01488   0.00644   0.0017   1.0000   0.2865
  -4.250  -0.5049   0.01412   0.00607   0.0035   1.0000   0.3593
  -4.000  -0.4891   0.01357   0.00584   0.0055   1.0000   0.4400
  -3.750  -0.4739   0.01318   0.00578   0.0078   1.0000   0.5101
  -3.500  -0.4488   0.01301   0.00580   0.0082   0.9942   0.5749
  -3.250  -0.4152   0.01299   0.00587   0.0073   0.9837   0.6342
  -3.000  -0.3817   0.01304   0.00591   0.0064   0.9741   0.6769
  -2.750  -0.3452   0.01306   0.00586   0.0048   0.9662   0.7014
  -2.500  -0.3104   0.01306   0.00577   0.0035   0.9570   0.7185
  -2.250  -0.2762   0.01305   0.00570   0.0023   0.9478   0.7340
  -2.000  -0.2406   0.01305   0.00561   0.0009   0.9400   0.7483
  -1.750  -0.2091   0.01305   0.00557   0.0003   0.9295   0.7626
  -1.500  -0.1776   0.01307   0.00556  -0.0001   0.9192   0.7784
  -1.250  -0.1465   0.01310   0.00555  -0.0003   0.9084   0.7956
  -1.000  -0.1158   0.01311   0.00554  -0.0003   0.8978   0.8117
  -0.750  -0.0872   0.01311   0.00553  -0.0001   0.8865   0.8251
  -0.500  -0.0586   0.01312   0.00553   0.0001   0.8762   0.8367
  -0.250  -0.0290   0.01311   0.00551   0.0000   0.8671   0.8474
   0.000   0.0000   0.01311   0.00549   0.0000   0.8578   0.8578
   0.250   0.0290   0.01311   0.00551   0.0000   0.8474   0.8671
   0.500   0.0586   0.01312   0.00553  -0.0001   0.8366   0.8762
   0.750   0.0872   0.01311   0.00553   0.0001   0.8249   0.8865
   1.000   0.1158   0.01311   0.00554   0.0003   0.8117   0.8978
   1.250   0.1465   0.01310   0.00555   0.0003   0.7956   0.9084
   1.500   0.1776   0.01307   0.00556   0.0001   0.7784   0.9192
   1.750   0.2091   0.01305   0.00557  -0.0003   0.7626   0.9295
   2.000   0.2406   0.01305   0.00561  -0.0009   0.7483   0.9399
   2.250   0.2762   0.01305   0.00570  -0.0023   0.7341   0.9478
   2.500   0.3105   0.01306   0.00577  -0.0035   0.7185   0.9570
   2.750   0.3452   0.01306   0.00586  -0.0048   0.7014   0.9662
   3.000   0.3817   0.01304   0.00590  -0.0064   0.6768   0.9741
   3.250   0.4152   0.01299   0.00587  -0.0073   0.6342   0.9837
   3.500   0.4488   0.01301   0.00580  -0.0083   0.5751   0.9942
   3.750   0.4738   0.01318   0.00578  -0.0078   0.5099   1.0000
   4.000   0.4891   0.01357   0.00584  -0.0055   0.4401   1.0000
   4.250   0.5049   0.01412   0.00607  -0.0035   0.3599   1.0000
   4.500   0.5205   0.01488   0.00644  -0.0018   0.2867   1.0000
   4.750   0.5379   0.01563   0.00691  -0.0003   0.2282   1.0000
   5.000   0.5566   0.01635   0.00742   0.0009   0.1682   1.0000
   5.250   0.5746   0.01731   0.00800   0.0022   0.1173   1.0000
   5.500   0.5936   0.01824   0.00878   0.0033   0.0946   1.0000
   5.750   0.6134   0.01914   0.00963   0.0045   0.0796   1.0000
   6.000   0.6334   0.02003   0.01055   0.0055   0.0676   1.0000
   6.250   0.6545   0.02086   0.01148   0.0065   0.0604   1.0000
   6.500   0.6739   0.02195   0.01257   0.0076   0.0554   1.0000
   6.750   0.6946   0.02308   0.01381   0.0087   0.0520   1.0000
   7.000   0.7160   0.02416   0.01500   0.0096   0.0479   1.0000
   7.250   0.7366   0.02524   0.01609   0.0104   0.0439   1.0000
   7.500   0.7575   0.02680   0.01775   0.0112   0.0414   1.0000
   7.750   0.7795   0.02840   0.01959   0.0121   0.0395   1.0000
   8.000   0.8008   0.03027   0.02179   0.0130   0.0378   1.0000
   8.250   0.8208   0.03233   0.02414   0.0140   0.0361   1.0000
   8.500   0.8387   0.03393   0.02594   0.0148   0.0337   1.0000
   8.750   0.8536   0.03625   0.02833   0.0156   0.0311   1.0000
   9.000   0.8658   0.03906   0.03164   0.0171   0.0300   1.0000
   9.250   0.8731   0.04219   0.03532   0.0187   0.0284   1.0000
   9.500   0.8778   0.04493   0.03848   0.0203   0.0260   1.0000
   9.750   0.8837   0.04685   0.04061   0.0215   0.0239   1.0000
  10.000   0.8886   0.04854   0.04239   0.0226   0.0224   1.0000
  10.250   0.8843   0.05155   0.04553   0.0239   0.0215   1.0000
  10.500   0.8682   0.05496   0.04916   0.0258   0.0211   1.0000
  10.750   0.8504   0.05872   0.05317   0.0263   0.0210   1.0000
  11.000   0.8307   0.06331   0.05797   0.0250   0.0209   1.0000
  11.250   0.8115   0.06868   0.06351   0.0222   0.0210   1.0000
  11.500   0.7906   0.07535   0.07029   0.0178   0.0212   1.0000
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