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SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD7080 (9.2%) (sd7080-il)
Reynolds number: 200,000
Max Cl/Cd: 69.43 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7080-il-200000.txt
Download as CSV file: xf-sd7080-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7080 (9.2%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4095   0.08735   0.08386  -0.0306   1.0000   0.0520
  -8.250  -0.4112   0.08407   0.08064  -0.0317   1.0000   0.0537
  -8.000  -0.4166   0.08087   0.07750  -0.0329   1.0000   0.0550
  -7.750  -0.4310   0.07780   0.07453  -0.0337   1.0000   0.0561
  -7.250  -0.4696   0.06881   0.06541  -0.0434   1.0000   0.0583
  -7.000  -0.4777   0.06590   0.06230  -0.0432   1.0000   0.0586
  -6.750  -0.4793   0.05973   0.05629  -0.0420   1.0000   0.0598
  -6.500  -0.4736   0.05747   0.05409  -0.0398   1.0000   0.0608
  -6.250  -0.4682   0.05529   0.05193  -0.0382   1.0000   0.0622
  -6.000  -0.4624   0.05265   0.04923  -0.0374   1.0000   0.0642
  -5.750  -0.4548   0.04921   0.04559  -0.0377   1.0000   0.0684
  -5.500  -0.4480   0.04425   0.04018  -0.0389   1.0000   0.0736
  -5.250  -0.4353   0.04201   0.03798  -0.0378   1.0000   0.0755
  -5.000  -0.4210   0.03981   0.03566  -0.0371   1.0000   0.0793
  -4.750  -0.3924   0.03643   0.03197  -0.0398   0.9973   0.0894
  -4.500  -0.3500   0.02516   0.01901  -0.0411   0.9954   0.0430
  -4.250  -0.3131   0.02139   0.01448  -0.0424   0.9926   0.0384
  -4.000  -0.2754   0.01957   0.01228  -0.0440   0.9885   0.0374
  -3.750  -0.2361   0.01814   0.01068  -0.0462   0.9849   0.0378
  -3.500  -0.1995   0.01702   0.00948  -0.0479   0.9801   0.0393
  -3.250  -0.1606   0.01632   0.00875  -0.0501   0.9748   0.0433
  -3.000  -0.1176   0.01561   0.00797  -0.0530   0.9711   0.0464
  -2.750  -0.0850   0.01460   0.00698  -0.0540   0.9636   0.0533
  -2.500  -0.0442   0.01334   0.00612  -0.0568   0.9592   0.1311
  -2.250  -0.0110   0.01226   0.00592  -0.0585   0.9524   0.3374
  -2.000   0.0241   0.01139   0.00587  -0.0602   0.9465   0.5505
  -1.750   0.0554   0.01077   0.00595  -0.0600   0.9406   0.7400
  -1.500   0.0854   0.01047   0.00591  -0.0592   0.9331   0.8467
  -1.250   0.1356   0.01026   0.00573  -0.0624   0.9305   0.9359
  -1.000   0.2036   0.01003   0.00539  -0.0700   0.9295   0.9822
  -0.750   0.2538   0.00983   0.00507  -0.0745   0.9222   1.0000
  -0.500   0.2907   0.00959   0.00472  -0.0760   0.9143   1.0000
  -0.250   0.3157   0.00943   0.00448  -0.0751   0.9013   1.0000
   0.000   0.3403   0.00929   0.00425  -0.0740   0.8880   1.0000
   0.250   0.3648   0.00915   0.00403  -0.0729   0.8742   1.0000
   0.500   0.3895   0.00902   0.00383  -0.0718   0.8595   1.0000
   0.750   0.4143   0.00891   0.00364  -0.0706   0.8438   1.0000
   1.000   0.4396   0.00881   0.00346  -0.0696   0.8271   1.0000
   1.250   0.4640   0.00878   0.00335  -0.0685   0.8066   1.0000
   1.500   0.4895   0.00876   0.00323  -0.0675   0.7858   1.0000
   1.750   0.5147   0.00879   0.00317  -0.0666   0.7627   1.0000
   2.000   0.5401   0.00887   0.00311  -0.0657   0.7389   1.0000
   2.250   0.5652   0.00899   0.00311  -0.0648   0.7130   1.0000
   2.500   0.5902   0.00916   0.00317  -0.0639   0.6863   1.0000
   2.750   0.6150   0.00935   0.00323  -0.0631   0.6591   1.0000
   3.000   0.6398   0.00958   0.00333  -0.0623   0.6319   1.0000
   3.250   0.6644   0.00982   0.00345  -0.0615   0.6044   1.0000
   3.500   0.6889   0.01009   0.00361  -0.0607   0.5769   1.0000
   3.750   0.7133   0.01038   0.00377  -0.0599   0.5497   1.0000
   4.000   0.7376   0.01068   0.00397  -0.0592   0.5221   1.0000
   4.250   0.7619   0.01099   0.00418  -0.0585   0.4951   1.0000
   4.500   0.7860   0.01132   0.00444  -0.0577   0.4684   1.0000
   4.750   0.8100   0.01167   0.00470  -0.0570   0.4427   1.0000
   5.000   0.8338   0.01205   0.00497  -0.0563   0.4177   1.0000
   5.250   0.8577   0.01241   0.00528  -0.0556   0.3924   1.0000
   5.500   0.8814   0.01281   0.00563  -0.0549   0.3681   1.0000
   5.750   0.9046   0.01325   0.00598  -0.0541   0.3450   1.0000
   6.000   0.9282   0.01366   0.00637  -0.0534   0.3213   1.0000
   6.250   0.9512   0.01413   0.00677  -0.0527   0.2991   1.0000
   6.500   0.9741   0.01459   0.00722  -0.0519   0.2764   1.0000
   6.750   0.9966   0.01509   0.00768  -0.0512   0.2544   1.0000
   7.000   1.0189   0.01561   0.00816  -0.0503   0.2328   1.0000
   7.250   1.0407   0.01618   0.00869  -0.0495   0.2127   1.0000
   7.500   1.0625   0.01675   0.00927  -0.0487   0.1930   1.0000
   7.750   1.0833   0.01742   0.00989  -0.0477   0.1748   1.0000
   8.000   1.1040   0.01810   0.01056  -0.0467   0.1570   1.0000
   8.250   1.1245   0.01873   0.01120  -0.0458   0.1379   1.0000
   8.500   1.1434   0.01948   0.01189  -0.0447   0.1193   1.0000
   8.750   1.1635   0.02014   0.01258  -0.0438   0.1010   1.0000
   9.000   1.1820   0.02095   0.01338  -0.0426   0.0855   1.0000
   9.250   1.1989   0.02188   0.01428  -0.0413   0.0704   1.0000
   9.500   1.2132   0.02307   0.01545  -0.0396   0.0536   1.0000
   9.750   1.2216   0.02477   0.01711  -0.0371   0.0383   1.0000
  10.000   1.2275   0.02654   0.01895  -0.0342   0.0321   1.0000
  10.250   1.2322   0.02809   0.02055  -0.0312   0.0289   1.0000
  10.500   1.2353   0.02990   0.02247  -0.0283   0.0263   1.0000
  10.750   1.2431   0.03134   0.02404  -0.0260   0.0245   1.0000
  11.000   1.2492   0.03293   0.02573  -0.0238   0.0231   1.0000
  11.250   1.2534   0.03480   0.02767  -0.0218   0.0220   1.0000
  11.500   1.2565   0.03728   0.03022  -0.0198   0.0212   1.0000
  11.750   1.2615   0.04017   0.03326  -0.0181   0.0206   1.0000
  12.000   1.2662   0.04240   0.03571  -0.0164   0.0201   1.0000
  12.250   1.2694   0.04497   0.03850  -0.0150   0.0199   1.0000
  12.500   1.2695   0.04779   0.04157  -0.0137   0.0195   1.0000
  12.750   1.2671   0.05098   0.04503  -0.0127   0.0194   1.0000
  13.000   1.2620   0.05448   0.04877  -0.0120   0.0193   1.0000
  13.250   1.2533   0.05851   0.05305  -0.0119   0.0192   1.0000
  13.500   1.2422   0.06293   0.05773  -0.0124   0.0192   1.0000
  13.750   1.2287   0.06793   0.06297  -0.0137   0.0192   1.0000
  14.000   1.2128   0.07356   0.06884  -0.0158   0.0192   1.0000
  14.250   1.1957   0.07975   0.07526  -0.0187   0.0193   1.0000
  14.500   1.1769   0.08665   0.08237  -0.0224   0.0194   1.0000
  14.750   1.1569   0.09426   0.09018  -0.0270   0.0196   1.0000
  15.000   1.1360   0.10263   0.09874  -0.0323   0.0197   1.0000
  15.250   1.1145   0.11173   0.10798  -0.0382   0.0200   1.0000
  15.500   1.0911   0.12190   0.11830  -0.0449   0.0202   1.0000
  15.750   1.0671   0.13291   0.12944  -0.0520   0.0204   1.0000
  16.000   1.0443   0.14433   0.14098  -0.0592   0.0208   1.0000
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