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

CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: CLARK X AIRFOIL (clarkx-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.42 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkx-il-1000000.txt
Download as CSV file: xf-clarkx-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK X AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.8537   0.09511   0.09300  -0.0420   1.0000   0.0171
 -15.750  -1.0922   0.05111   0.04855  -0.0719   1.0000   0.0155
 -15.500  -1.1502   0.03440   0.03138  -0.0898   1.0000   0.0153
 -15.250  -1.1555   0.03165   0.02851  -0.0903   1.0000   0.0155
 -15.000  -1.1562   0.02998   0.02674  -0.0888   1.0000   0.0157
 -14.750  -1.1509   0.02865   0.02531  -0.0872   1.0000   0.0161
 -14.500  -1.1432   0.02750   0.02406  -0.0855   1.0000   0.0165
 -14.250  -1.1351   0.02651   0.02297  -0.0834   1.0000   0.0168
 -14.000  -1.1259   0.02566   0.02202  -0.0812   1.0000   0.0171
 -13.750  -1.1229   0.02450   0.02075  -0.0781   1.0000   0.0175
 -13.500  -1.1185   0.02348   0.01966  -0.0750   1.0000   0.0180
 -13.250  -1.1081   0.02289   0.01904  -0.0726   1.0000   0.0185
 -13.000  -1.0839   0.02239   0.01851  -0.0726   0.9993   0.0191
 -12.750  -1.0533   0.02185   0.01791  -0.0739   0.9980   0.0198
 -12.500  -1.0225   0.02129   0.01726  -0.0752   0.9967   0.0204
 -12.250  -0.9908   0.02080   0.01667  -0.0766   0.9954   0.0209
 -12.000  -0.9629   0.01944   0.01521  -0.0780   0.9941   0.0219
 -11.750  -0.9332   0.01896   0.01470  -0.0790   0.9922   0.0226
 -11.500  -0.9025   0.01857   0.01428  -0.0800   0.9902   0.0233
 -11.250  -0.8709   0.01819   0.01385  -0.0812   0.9884   0.0240
 -11.000  -0.8383   0.01783   0.01341  -0.0825   0.9868   0.0248
 -10.750  -0.8047   0.01756   0.01307  -0.0840   0.9856   0.0252
 -10.500  -0.7751   0.01625   0.01165  -0.0855   0.9843   0.0264
 -10.250  -0.7416   0.01581   0.01119  -0.0870   0.9833   0.0272
 -10.000  -0.7127   0.01551   0.01086  -0.0875   0.9799   0.0280
  -9.750  -0.6827   0.01519   0.01050  -0.0882   0.9767   0.0288
  -9.500  -0.6518   0.01483   0.01008  -0.0890   0.9738   0.0296
  -9.250  -0.6210   0.01449   0.00968  -0.0898   0.9711   0.0301
  -9.000  -0.5964   0.01384   0.00893  -0.0894   0.9656   0.0308
  -8.750  -0.5716   0.01316   0.00821  -0.0891   0.9600   0.0320
  -8.500  -0.5439   0.01282   0.00785  -0.0891   0.9556   0.0328
  -8.250  -0.5189   0.01256   0.00756  -0.0886   0.9487   0.0336
  -8.000  -0.4923   0.01228   0.00722  -0.0883   0.9430   0.0345
  -7.750  -0.4664   0.01198   0.00687  -0.0879   0.9365   0.0352
  -7.500  -0.4401   0.01174   0.00656  -0.0876   0.9296   0.0359
  -7.250  -0.4131   0.01157   0.00633  -0.0873   0.9232   0.0363
  -7.000  -0.3895   0.01079   0.00547  -0.0866   0.9153   0.0378
  -6.750  -0.3631   0.01047   0.00511  -0.0863   0.9086   0.0389
  -6.500  -0.3364   0.01023   0.00485  -0.0861   0.9006   0.0400
  -6.250  -0.3093   0.01004   0.00460  -0.0859   0.8936   0.0412
  -6.000  -0.2822   0.00984   0.00436  -0.0856   0.8855   0.0423
  -5.750  -0.2550   0.00967   0.00412  -0.0854   0.8782   0.0431
  -5.500  -0.2285   0.00931   0.00371  -0.0852   0.8698   0.0446
  -5.250  -0.2016   0.00905   0.00341  -0.0849   0.8621   0.0468
  -5.000  -0.1742   0.00888   0.00323  -0.0848   0.8536   0.0486
  -4.750  -0.1466   0.00876   0.00306  -0.0846   0.8459   0.0505
  -4.500  -0.1188   0.00867   0.00293  -0.0845   0.8373   0.0518
  -4.250  -0.0920   0.00838   0.00261  -0.0843   0.8294   0.0560
  -4.000  -0.0644   0.00826   0.00247  -0.0842   0.8208   0.0590
  -3.750  -0.0365   0.00818   0.00234  -0.0841   0.8127   0.0613
  -3.500  -0.0092   0.00799   0.00214  -0.0839   0.8041   0.0663
  -3.250   0.0185   0.00788   0.00202  -0.0838   0.7958   0.0709
  -3.000   0.0462   0.00780   0.00189  -0.0837   0.7872   0.0753
  -2.750   0.0738   0.00766   0.00177  -0.0836   0.7784   0.0827
  -2.500   0.1012   0.00757   0.00166  -0.0834   0.7694   0.0912
  -2.250   0.1288   0.00744   0.00157  -0.0833   0.7596   0.1050
  -2.000   0.1561   0.00732   0.00149  -0.0832   0.7504   0.1281
  -1.750   0.1834   0.00718   0.00141  -0.0830   0.7410   0.1539
  -1.500   0.2106   0.00701   0.00134  -0.0829   0.7324   0.1899
  -1.250   0.2373   0.00681   0.00131  -0.0828   0.7236   0.2538
  -1.000   0.2650   0.00670   0.00129  -0.0827   0.7148   0.2895
  -0.750   0.2923   0.00664   0.00127  -0.0826   0.7060   0.3188
  -0.500   0.3199   0.00655   0.00125  -0.0825   0.6968   0.3487
  -0.250   0.3470   0.00643   0.00124  -0.0824   0.6878   0.3926
   0.000   0.3734   0.00622   0.00124  -0.0821   0.6781   0.4755
   0.500   0.4237   0.00567   0.00129  -0.0811   0.6583   0.6972
   0.750   0.4465   0.00539   0.00135  -0.0798   0.6463   0.8181
   1.000   0.4689   0.00526   0.00144  -0.0783   0.6320   0.9113
   1.250   0.5010   0.00533   0.00152  -0.0788   0.6167   0.9630
   1.500   0.5389   0.00544   0.00157  -0.0809   0.6029   0.9835
   1.750   0.5775   0.00554   0.00161  -0.0833   0.5902   0.9902
   2.000   0.6158   0.00566   0.00166  -0.0856   0.5768   0.9954
   2.250   0.6570   0.00578   0.00171  -0.0886   0.5614   0.9999
   2.500   0.6817   0.00590   0.00176  -0.0879   0.5467   1.0000
   2.750   0.7060   0.00602   0.00182  -0.0872   0.5322   1.0000
   3.000   0.7302   0.00615   0.00189  -0.0864   0.5179   1.0000
   3.250   0.7544   0.00629   0.00197  -0.0857   0.5032   1.0000
   3.500   0.7786   0.00644   0.00206  -0.0849   0.4880   1.0000
   3.750   0.8027   0.00660   0.00216  -0.0842   0.4723   1.0000
   4.000   0.8267   0.00677   0.00227  -0.0834   0.4562   1.0000
   4.250   0.8508   0.00695   0.00239  -0.0826   0.4392   1.0000
   4.500   0.8747   0.00715   0.00252  -0.0818   0.4208   1.0000
   4.750   0.8987   0.00737   0.00267  -0.0811   0.4021   1.0000
   5.000   0.9224   0.00762   0.00283  -0.0803   0.3821   1.0000
   5.250   0.9450   0.00796   0.00303  -0.0794   0.3519   1.0000
   5.500   0.9679   0.00831   0.00324  -0.0785   0.3240   1.0000
   5.750   0.9912   0.00862   0.00345  -0.0777   0.3033   1.0000
   6.000   1.0151   0.00892   0.00367  -0.0771   0.2825   1.0000
   6.250   1.0385   0.00924   0.00390  -0.0763   0.2617   1.0000
   6.500   1.0616   0.00960   0.00415  -0.0756   0.2405   1.0000
   6.750   1.0846   0.00996   0.00442  -0.0748   0.2198   1.0000
   7.250   1.1297   0.01074   0.00501  -0.0732   0.1821   1.0000
   7.500   1.1520   0.01114   0.00533  -0.0723   0.1639   1.0000
   7.750   1.1731   0.01163   0.00570  -0.0713   0.1430   1.0000
   8.000   1.1904   0.01239   0.00623  -0.0697   0.1036   1.0000
   8.250   1.2006   0.01366   0.00714  -0.0671   0.0499   1.0000
   8.500   1.2166   0.01447   0.00782  -0.0653   0.0315   1.0000
   8.750   1.2355   0.01505   0.00838  -0.0639   0.0262   1.0000
   9.000   1.2555   0.01552   0.00886  -0.0627   0.0237   1.0000
   9.250   1.2729   0.01609   0.00944  -0.0611   0.0213   1.0000
   9.500   1.2913   0.01652   0.00991  -0.0596   0.0201   1.0000
   9.750   1.3083   0.01704   0.01045  -0.0580   0.0189   1.0000
  10.000   1.3219   0.01779   0.01123  -0.0558   0.0176   1.0000
  10.250   1.3387   0.01833   0.01182  -0.0543   0.0170   1.0000
  10.500   1.3551   0.01890   0.01243  -0.0527   0.0163   1.0000
  10.750   1.3707   0.01952   0.01308  -0.0511   0.0156   1.0000
  11.000   1.3847   0.02025   0.01384  -0.0494   0.0149   1.0000
  11.250   1.3931   0.02137   0.01502  -0.0470   0.0141   1.0000
  11.500   1.4055   0.02225   0.01597  -0.0453   0.0138   1.0000
  11.750   1.4189   0.02308   0.01685  -0.0438   0.0135   1.0000
  12.000   1.4309   0.02402   0.01786  -0.0422   0.0131   1.0000
  12.250   1.4422   0.02505   0.01894  -0.0406   0.0127   1.0000
  12.500   1.4526   0.02617   0.02012  -0.0391   0.0123   1.0000
  12.750   1.4620   0.02741   0.02142  -0.0376   0.0120   1.0000
  13.000   1.4686   0.02890   0.02296  -0.0360   0.0117   1.0000
  13.250   1.4700   0.03089   0.02504  -0.0343   0.0114   1.0000
  13.500   1.4641   0.03362   0.02788  -0.0323   0.0111   1.0000
  13.750   1.4730   0.03512   0.02945  -0.0314   0.0109   1.0000
  14.000   1.4802   0.03683   0.03124  -0.0305   0.0108   1.0000
  14.250   1.4854   0.03878   0.03326  -0.0297   0.0106   1.0000
  14.500   1.4897   0.04086   0.03542  -0.0290   0.0103   1.0000
  14.750   1.4922   0.04319   0.03785  -0.0283   0.0101   1.0000
  15.000   1.4939   0.04570   0.04043  -0.0279   0.0099   1.0000
  15.250   1.4944   0.04840   0.04322  -0.0275   0.0098   1.0000
  15.500   1.4939   0.05132   0.04622  -0.0273   0.0096   1.0000
  15.750   1.4924   0.05447   0.04946  -0.0274   0.0095   1.0000
  16.000   1.4900   0.05782   0.05289  -0.0275   0.0093   1.0000
  16.250   1.4857   0.06149   0.05664  -0.0279   0.0092   1.0000
  16.500   1.4797   0.06549   0.06074  -0.0285   0.0091   1.0000
  16.750   1.4714   0.06991   0.06526  -0.0293   0.0090   1.0000
  17.000   1.4611   0.07468   0.07012  -0.0302   0.0089   1.0000
  17.250   1.4483   0.07987   0.07542  -0.0314   0.0088   1.0000
  17.500   1.4326   0.08553   0.08120  -0.0327   0.0087   1.0000
<< Back to CLARK X AIRFOIL (clarkx-il)

Polar data table (+)

Polar graphs


<< Back to CLARK X AIRFOIL (clarkx-il)