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

SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SD7080 (9.2%) (sd7080-il)
Reynolds number: 500,000
Max Cl/Cd: 84.91 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7080-il-500000-n5.txt
Download as CSV file: xf-sd7080-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4420   0.08442   0.08211  -0.0314   1.0000   0.0108
  -9.000  -0.4445   0.08034   0.07807  -0.0332   1.0000   0.0110
  -8.750  -0.4571   0.07448   0.07225  -0.0358   1.0000   0.0105
  -8.500  -0.5539   0.04470   0.04229  -0.0560   0.9959   0.0093
  -8.250  -0.5480   0.03481   0.03174  -0.0641   0.9878   0.0093
  -8.000  -0.5292   0.02904   0.02538  -0.0681   0.9840   0.0094
  -7.750  -0.5089   0.02526   0.02117  -0.0697   0.9795   0.0096
  -7.500  -0.4841   0.02291   0.01850  -0.0708   0.9755   0.0097
  -7.250  -0.4563   0.02124   0.01660  -0.0719   0.9725   0.0100
  -7.000  -0.4283   0.01968   0.01479  -0.0727   0.9695   0.0102
  -6.750  -0.4037   0.01848   0.01339  -0.0726   0.9643   0.0105
  -6.500  -0.3766   0.01732   0.01205  -0.0729   0.9601   0.0107
  -6.250  -0.3484   0.01624   0.01078  -0.0732   0.9567   0.0110
  -6.000  -0.3243   0.01537   0.00976  -0.0726   0.9506   0.0112
  -5.750  -0.2983   0.01456   0.00881  -0.0723   0.9456   0.0115
  -5.500  -0.2719   0.01389   0.00804  -0.0721   0.9410   0.0119
  -5.250  -0.2468   0.01331   0.00737  -0.0715   0.9348   0.0124
  -5.000  -0.2209   0.01265   0.00660  -0.0710   0.9296   0.0125
  -4.750  -0.1957   0.01204   0.00592  -0.0705   0.9233   0.0127
  -4.500  -0.1700   0.01151   0.00530  -0.0700   0.9169   0.0129
  -4.250  -0.1441   0.01105   0.00477  -0.0695   0.9105   0.0132
  -4.000  -0.1181   0.01063   0.00429  -0.0690   0.9031   0.0135
  -3.750  -0.0922   0.01009   0.00368  -0.0685   0.8960   0.0141
  -3.500  -0.0658   0.00973   0.00326  -0.0681   0.8880   0.0150
  -3.250  -0.0390   0.00946   0.00293  -0.0678   0.8796   0.0158
  -3.000  -0.0121   0.00923   0.00264  -0.0674   0.8708   0.0167
  -2.750   0.0149   0.00904   0.00239  -0.0671   0.8600   0.0180
  -2.500   0.0419   0.00884   0.00215  -0.0667   0.8483   0.0210
  -2.250   0.0687   0.00858   0.00193  -0.0664   0.8352   0.0375
  -2.000   0.0952   0.00829   0.00174  -0.0661   0.8201   0.0791
  -1.750   0.1216   0.00800   0.00159  -0.0658   0.8031   0.1341
  -1.500   0.1481   0.00779   0.00146  -0.0655   0.7845   0.1859
  -1.250   0.1743   0.00756   0.00136  -0.0652   0.7638   0.2512
  -1.000   0.1995   0.00712   0.00130  -0.0649   0.7423   0.3886
  -0.750   0.2245   0.00674   0.00127  -0.0644   0.7200   0.5242
  -0.500   0.2498   0.00659   0.00127  -0.0638   0.6973   0.6077
  -0.250   0.2755   0.00653   0.00128  -0.0633   0.6741   0.6639
   0.000   0.3008   0.00649   0.00130  -0.0626   0.6510   0.7179
   0.500   0.3504   0.00649   0.00138  -0.0609   0.6036   0.8129
   0.750   0.3742   0.00651   0.00142  -0.0598   0.5808   0.8575
   1.000   0.3977   0.00655   0.00147  -0.0586   0.5584   0.9041
   1.250   0.4274   0.00663   0.00150  -0.0587   0.5352   0.9494
   1.500   0.4649   0.00678   0.00153  -0.0608   0.5099   0.9834
   1.750   0.4970   0.00695   0.00158  -0.0618   0.4860   1.0000
   2.000   0.5227   0.00713   0.00165  -0.0614   0.4646   1.0000
   2.250   0.5485   0.00732   0.00173  -0.0610   0.4429   1.0000
   2.500   0.5745   0.00751   0.00182  -0.0607   0.4220   1.0000
   2.750   0.6005   0.00771   0.00193  -0.0603   0.4009   1.0000
   3.000   0.6265   0.00792   0.00205  -0.0600   0.3810   1.0000
   3.250   0.6526   0.00813   0.00217  -0.0597   0.3608   1.0000
   3.500   0.6785   0.00836   0.00232  -0.0594   0.3412   1.0000
   3.750   0.7045   0.00859   0.00247  -0.0591   0.3224   1.0000
   4.000   0.7305   0.00882   0.00263  -0.0588   0.3039   1.0000
   4.250   0.7564   0.00907   0.00280  -0.0585   0.2857   1.0000
   4.750   0.8080   0.00958   0.00320  -0.0579   0.2524   1.0000
   5.000   0.8337   0.00985   0.00341  -0.0575   0.2352   1.0000
   5.250   0.8593   0.01012   0.00364  -0.0572   0.2203   1.0000
   5.500   0.8847   0.01042   0.00389  -0.0569   0.2039   1.0000
   5.750   0.9096   0.01077   0.00416  -0.0565   0.1855   1.0000
   6.000   0.9344   0.01112   0.00445  -0.0560   0.1671   1.0000
   6.250   0.9594   0.01146   0.00474  -0.0556   0.1529   1.0000
   6.500   0.9837   0.01185   0.00507  -0.0552   0.1350   1.0000
   6.750   1.0072   0.01233   0.00545  -0.0546   0.1139   1.0000
   7.000   1.0309   0.01279   0.00583  -0.0541   0.0962   1.0000
   7.250   1.0546   0.01324   0.00623  -0.0535   0.0826   1.0000
   7.500   1.0781   0.01368   0.00664  -0.0530   0.0711   1.0000
   7.750   1.1008   0.01422   0.00711  -0.0523   0.0571   1.0000
   8.000   1.1232   0.01476   0.00762  -0.0516   0.0456   1.0000
   8.250   1.1451   0.01534   0.00816  -0.0508   0.0353   1.0000
   8.500   1.1661   0.01600   0.00877  -0.0500   0.0250   1.0000
   8.750   1.1864   0.01671   0.00944  -0.0490   0.0150   1.0000
   9.000   1.2057   0.01751   0.01021  -0.0478   0.0092   1.0000
   9.250   1.2263   0.01813   0.01088  -0.0469   0.0080   1.0000
   9.500   1.2456   0.01885   0.01169  -0.0457   0.0069   1.0000
   9.750   1.2646   0.01957   0.01249  -0.0445   0.0064   1.0000
  10.000   1.2833   0.02027   0.01329  -0.0433   0.0061   1.0000
  10.250   1.3012   0.02099   0.01411  -0.0420   0.0058   1.0000
  10.500   1.3177   0.02179   0.01501  -0.0405   0.0056   1.0000
  10.750   1.3327   0.02264   0.01596  -0.0389   0.0054   1.0000
  11.000   1.3448   0.02352   0.01695  -0.0367   0.0052   1.0000
  11.250   1.3541   0.02449   0.01803  -0.0343   0.0050   1.0000
  11.500   1.3622   0.02553   0.01918  -0.0318   0.0049   1.0000
  11.750   1.3698   0.02664   0.02039  -0.0295   0.0047   1.0000
  12.000   1.3747   0.02796   0.02182  -0.0271   0.0046   1.0000
  12.250   1.3767   0.02954   0.02352  -0.0247   0.0044   1.0000
  12.500   1.3781   0.03125   0.02535  -0.0225   0.0043   1.0000
  12.750   1.3749   0.03345   0.02768  -0.0204   0.0042   1.0000
  13.000   1.3688   0.03608   0.03046  -0.0187   0.0040   1.0000
  13.250   1.3671   0.03854   0.03306  -0.0177   0.0040   1.0000
  13.500   1.3652   0.04121   0.03586  -0.0171   0.0040   1.0000
  13.750   1.3620   0.04426   0.03905  -0.0170   0.0039   1.0000
  14.000   1.3565   0.04783   0.04276  -0.0174   0.0039   1.0000
  14.250   1.3510   0.05167   0.04674  -0.0183   0.0039   1.0000
  14.500   1.3458   0.05574   0.05099  -0.0196   0.0038   1.0000
  14.750   1.3342   0.06099   0.05639  -0.0216   0.0039   1.0000
  15.000   1.3248   0.06622   0.06177  -0.0239   0.0038   1.0000
  15.250   1.3136   0.07197   0.06767  -0.0266   0.0038   1.0000
  15.500   1.3008   0.07824   0.07409  -0.0297   0.0038   1.0000
  15.750   1.2874   0.08485   0.08083  -0.0331   0.0038   1.0000
  16.000   1.2741   0.09163   0.08776  -0.0367   0.0038   1.0000
  16.250   1.2606   0.09866   0.09493  -0.0404   0.0038   1.0000
  16.500   1.2462   0.10600   0.10239  -0.0443   0.0038   1.0000
<< Back to SD7080 (9.2%) (sd7080-il)

Polar data table (+)

Polar graphs


<< Back to SD7080 (9.2%) (sd7080-il)