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

Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Curtis C-72 (curtisc72-il)
Reynolds number: 200,000
Max Cl/Cd: 73.28 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-curtisc72-il-200000-n5.txt
Download as CSV file: xf-curtisc72-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Curtis C-72                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3938   0.08903   0.08526  -0.0451   1.0000   0.0320
 -11.500  -0.4015   0.08475   0.08104  -0.0465   1.0000   0.0324
 -11.250  -0.4153   0.08019   0.07656  -0.0476   1.0000   0.0326
 -11.000  -0.4383   0.07584   0.07231  -0.0475   1.0000   0.0326
 -10.750  -0.5041   0.04281   0.03858  -0.0857   0.9785   0.0322
 -10.500  -0.4894   0.03599   0.03108  -0.0918   0.9715   0.0331
 -10.250  -0.4691   0.03195   0.02645  -0.0944   0.9645   0.0342
 -10.000  -0.4409   0.02885   0.02278  -0.0970   0.9609   0.0350
  -9.750  -0.4171   0.02685   0.02035  -0.0975   0.9539   0.0354
  -9.500  -0.3885   0.02480   0.01803  -0.0987   0.9495   0.0359
  -9.250  -0.3576   0.02342   0.01654  -0.1000   0.9460   0.0368
  -9.000  -0.3315   0.02248   0.01550  -0.1001   0.9390   0.0376
  -8.750  -0.3007   0.02143   0.01428  -0.1010   0.9344   0.0384
  -8.500  -0.2701   0.02036   0.01304  -0.1017   0.9300   0.0391
  -8.250  -0.2429   0.01945   0.01198  -0.1016   0.9229   0.0397
  -8.000  -0.2122   0.01856   0.01095  -0.1022   0.9180   0.0404
  -7.750  -0.1833   0.01779   0.01006  -0.1024   0.9120   0.0411
  -7.500  -0.1552   0.01712   0.00929  -0.1024   0.9052   0.0419
  -7.250  -0.1242   0.01654   0.00859  -0.1029   0.9001   0.0428
  -7.000  -0.0986   0.01586   0.00792  -0.1025   0.8920   0.0441
  -6.750  -0.0696   0.01532   0.00735  -0.1026   0.8857   0.0452
  -6.500  -0.0424   0.01488   0.00687  -0.1024   0.8780   0.0463
  -6.250  -0.0144   0.01446   0.00640  -0.1022   0.8707   0.0477
  -6.000   0.0133   0.01410   0.00597  -0.1021   0.8633   0.0492
  -5.750   0.0409   0.01377   0.00558  -0.1018   0.8553   0.0510
  -5.500   0.0687   0.01343   0.00522  -0.1017   0.8477   0.0538
  -5.250   0.0962   0.01316   0.00494  -0.1015   0.8394   0.0587
  -5.000   0.1239   0.01288   0.00467  -0.1013   0.8313   0.0673
  -4.750   0.1515   0.01261   0.00439  -0.1010   0.8228   0.0821
  -4.500   0.1787   0.01234   0.00415  -0.1008   0.8131   0.1014
  -4.250   0.2062   0.01206   0.00392  -0.1006   0.8027   0.1293
  -4.000   0.2329   0.01176   0.00372  -0.1002   0.7894   0.1717
  -3.750   0.2591   0.01141   0.00357  -0.0999   0.7756   0.2367
  -3.500   0.2853   0.01105   0.00348  -0.0996   0.7634   0.3270
  -3.250   0.3117   0.01081   0.00349  -0.0992   0.7533   0.4155
  -3.000   0.3386   0.01071   0.00348  -0.0989   0.7429   0.4711
  -2.750   0.3655   0.01065   0.00346  -0.0985   0.7325   0.5069
  -2.500   0.3926   0.01060   0.00342  -0.0981   0.7226   0.5362
  -2.250   0.4192   0.01054   0.00341  -0.0977   0.7116   0.5693
  -2.000   0.4455   0.01046   0.00342  -0.0972   0.7006   0.6062
  -1.750   0.4716   0.01038   0.00341  -0.0966   0.6901   0.6456
  -1.500   0.4969   0.01027   0.00342  -0.0959   0.6790   0.6917
  -1.250   0.5210   0.01008   0.00344  -0.0948   0.6674   0.7575
  -1.000   0.5611   0.00978   0.00341  -0.0966   0.6547   0.9775
  -0.750   0.5896   0.00989   0.00340  -0.0968   0.6425   1.0000
  -0.500   0.6162   0.01001   0.00343  -0.0965   0.6299   1.0000
  -0.250   0.6426   0.01015   0.00347  -0.0962   0.6163   1.0000
   0.000   0.6688   0.01029   0.00352  -0.0958   0.6019   1.0000
   0.250   0.6948   0.01045   0.00359  -0.0954   0.5872   1.0000
   0.500   0.7208   0.01062   0.00368  -0.0951   0.5725   1.0000
   0.750   0.7465   0.01080   0.00377  -0.0947   0.5569   1.0000
   1.000   0.7720   0.01100   0.00388  -0.0942   0.5399   1.0000
   1.250   0.7971   0.01121   0.00401  -0.0937   0.5223   1.0000
   1.500   0.8222   0.01145   0.00416  -0.0932   0.5049   1.0000
   1.750   0.8469   0.01170   0.00433  -0.0927   0.4870   1.0000
   2.000   0.8713   0.01198   0.00452  -0.0922   0.4690   1.0000
   2.250   0.8957   0.01226   0.00472  -0.0916   0.4512   1.0000
   2.500   0.9199   0.01256   0.00496  -0.0911   0.4340   1.0000
   2.750   0.9438   0.01288   0.00520  -0.0905   0.4174   1.0000
   3.000   0.9676   0.01322   0.00547  -0.0899   0.4017   1.0000
   3.250   0.9910   0.01358   0.00575  -0.0893   0.3857   1.0000
   3.500   1.0139   0.01396   0.00606  -0.0886   0.3687   1.0000
   3.750   1.0368   0.01434   0.00638  -0.0880   0.3532   1.0000
   4.000   1.0600   0.01472   0.00671  -0.0874   0.3415   1.0000
   4.250   1.0837   0.01506   0.00706  -0.0869   0.3316   1.0000
   4.500   1.1073   0.01541   0.00742  -0.0864   0.3232   1.0000
   4.750   1.1306   0.01578   0.00779  -0.0858   0.3145   1.0000
   5.000   1.1539   0.01613   0.00819  -0.0853   0.3058   1.0000
   5.250   1.1761   0.01654   0.00859  -0.0846   0.2963   1.0000
   5.500   1.1990   0.01689   0.00900  -0.0840   0.2861   1.0000
   5.750   1.2210   0.01730   0.00943  -0.0833   0.2765   1.0000
   6.000   1.2424   0.01771   0.00989  -0.0826   0.2661   1.0000
   6.250   1.2640   0.01811   0.01035  -0.0818   0.2550   1.0000
   6.500   1.2842   0.01857   0.01083  -0.0809   0.2422   1.0000
   6.750   1.3032   0.01908   0.01135  -0.0798   0.2271   1.0000
   7.000   1.3194   0.01971   0.01194  -0.0784   0.2066   1.0000
   7.250   1.3320   0.02049   0.01260  -0.0764   0.1813   1.0000
   7.500   1.3420   0.02144   0.01341  -0.0741   0.1580   1.0000
   7.750   1.3527   0.02240   0.01429  -0.0721   0.1398   1.0000
   8.000   1.3642   0.02333   0.01519  -0.0702   0.1267   1.0000
   8.250   1.3757   0.02429   0.01616  -0.0684   0.1165   1.0000
   8.500   1.3857   0.02535   0.01721  -0.0666   0.1072   1.0000
   8.750   1.3973   0.02634   0.01825  -0.0650   0.0985   1.0000
   9.000   1.4071   0.02747   0.01941  -0.0634   0.0909   1.0000
   9.250   1.4157   0.02872   0.02068  -0.0617   0.0830   1.0000
   9.500   1.4252   0.02995   0.02198  -0.0603   0.0750   1.0000
   9.750   1.4326   0.03138   0.02345  -0.0588   0.0665   1.0000
  10.000   1.4386   0.03297   0.02505  -0.0574   0.0568   1.0000
  10.250   1.4422   0.03482   0.02690  -0.0559   0.0474   1.0000
  10.500   1.4436   0.03693   0.02902  -0.0545   0.0402   1.0000
  11.000   1.4441   0.04164   0.03383  -0.0522   0.0317   1.0000
  11.250   1.4418   0.04439   0.03665  -0.0512   0.0292   1.0000
  11.500   1.4416   0.04703   0.03943  -0.0506   0.0273   1.0000
  11.750   1.4394   0.04997   0.04249  -0.0500   0.0258   1.0000
  12.000   1.4349   0.05327   0.04589  -0.0497   0.0246   1.0000
  12.250   1.4288   0.05691   0.04964  -0.0497   0.0237   1.0000
  12.500   1.4251   0.06040   0.05327  -0.0498   0.0228   1.0000
  12.750   1.4201   0.06418   0.05720  -0.0502   0.0220   1.0000
  13.000   1.4139   0.06825   0.06141  -0.0508   0.0213   1.0000
  13.250   1.4064   0.07263   0.06592  -0.0516   0.0207   1.0000
  13.500   1.3974   0.07734   0.07076  -0.0527   0.0201   1.0000
  13.750   1.3868   0.08245   0.07598  -0.0540   0.0197   1.0000
  14.000   1.3757   0.08774   0.08138  -0.0555   0.0193   1.0000
<< Back to Curtis C-72 (curtisc72-il)

Polar data table (+)

Polar graphs


<< Back to Curtis C-72 (curtisc72-il)