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SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SD7003-085-88 (sd7003-il)
Reynolds number: 500,000
Max Cl/Cd: 75.99 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7003-il-500000-n5.txt
Download as CSV file: xf-sd7003-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7003-085-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.9024   0.04286   0.04002  -0.0415   1.0000   0.0052
 -11.250  -0.9194   0.03849   0.03542  -0.0428   1.0000   0.0052
 -11.000  -0.9227   0.03480   0.03146  -0.0432   1.0000   0.0053
 -10.750  -0.9166   0.03203   0.02844  -0.0431   1.0000   0.0054
 -10.500  -0.9079   0.02933   0.02545  -0.0427   1.0000   0.0055
 -10.250  -0.8941   0.02724   0.02311  -0.0423   1.0000   0.0056
 -10.000  -0.8781   0.02540   0.02103  -0.0417   1.0000   0.0058
  -9.750  -0.8604   0.02372   0.01912  -0.0412   1.0000   0.0060
  -9.500  -0.8413   0.02223   0.01741  -0.0406   1.0000   0.0061
  -9.250  -0.8210   0.02094   0.01591  -0.0400   1.0000   0.0063
  -9.000  -0.7998   0.01978   0.01457  -0.0394   1.0000   0.0064
  -8.750  -0.7777   0.01879   0.01342  -0.0388   1.0000   0.0066
  -8.500  -0.7560   0.01769   0.01217  -0.0381   1.0000   0.0068
  -8.250  -0.7337   0.01669   0.01106  -0.0375   1.0000   0.0072
  -8.000  -0.7104   0.01600   0.01029  -0.0369   1.0000   0.0076
  -7.750  -0.6866   0.01541   0.00960  -0.0363   1.0000   0.0081
  -7.500  -0.6628   0.01480   0.00891  -0.0357   1.0000   0.0087
  -7.250  -0.6389   0.01419   0.00820  -0.0350   1.0000   0.0092
  -7.000  -0.6151   0.01357   0.00749  -0.0343   1.0000   0.0097
  -6.750  -0.5911   0.01296   0.00685  -0.0337   1.0000   0.0106
  -6.500  -0.5668   0.01250   0.00632  -0.0330   1.0000   0.0117
  -6.250  -0.5423   0.01208   0.00583  -0.0323   1.0000   0.0130
  -6.000  -0.5180   0.01161   0.00535  -0.0317   1.0000   0.0150
  -5.750  -0.4934   0.01126   0.00497  -0.0310   1.0000   0.0175
  -5.500  -0.4691   0.01090   0.00462  -0.0304   1.0000   0.0207
  -5.250  -0.4381   0.01056   0.00426  -0.0311   0.9978   0.0245
  -5.000  -0.4029   0.01026   0.00395  -0.0327   0.9940   0.0286
  -4.750  -0.3692   0.00995   0.00366  -0.0340   0.9887   0.0347
  -4.500  -0.3336   0.00966   0.00340  -0.0357   0.9838   0.0422
  -4.250  -0.3010   0.00943   0.00316  -0.0366   0.9758   0.0487
  -4.000  -0.2672   0.00916   0.00291  -0.0378   0.9672   0.0562
  -3.750  -0.2328   0.00892   0.00268  -0.0391   0.9557   0.0642
  -3.500  -0.1984   0.00870   0.00245  -0.0404   0.9400   0.0738
  -3.250  -0.1648   0.00848   0.00224  -0.0414   0.9182   0.0864
  -3.000  -0.1349   0.00828   0.00204  -0.0417   0.8903   0.1044
  -2.750  -0.1078   0.00814   0.00187  -0.0413   0.8598   0.1254
  -2.500  -0.0816   0.00801   0.00172  -0.0407   0.8293   0.1520
  -2.250  -0.0555   0.00789   0.00159  -0.0402   0.8000   0.1841
  -2.000  -0.0292   0.00778   0.00148  -0.0398   0.7713   0.2181
  -1.750  -0.0029   0.00765   0.00138  -0.0394   0.7440   0.2618
  -1.500   0.0237   0.00755   0.00130  -0.0390   0.7171   0.3044
  -1.250   0.0503   0.00745   0.00123  -0.0387   0.6905   0.3479
  -1.000   0.0769   0.00732   0.00118  -0.0384   0.6641   0.4048
  -0.750   0.1034   0.00715   0.00115  -0.0381   0.6380   0.4747
  -0.500   0.1297   0.00701   0.00113  -0.0378   0.6122   0.5455
   0.000   0.1822   0.00683   0.00117  -0.0369   0.5606   0.6746
   0.250   0.2085   0.00682   0.00120  -0.0364   0.5362   0.7211
   0.750   0.2607   0.00687   0.00129  -0.0352   0.4887   0.7951
   1.000   0.2863   0.00692   0.00134  -0.0346   0.4659   0.8263
   1.250   0.3117   0.00697   0.00140  -0.0338   0.4435   0.8564
   1.500   0.3364   0.00704   0.00145  -0.0328   0.4214   0.8869
   1.750   0.3612   0.00710   0.00150  -0.0319   0.4000   0.9197
   2.000   0.3907   0.00721   0.00155  -0.0320   0.3770   0.9543
   2.250   0.4276   0.00735   0.00160  -0.0339   0.3526   0.9908
   2.500   0.4562   0.00753   0.00169  -0.0341   0.3318   1.0000
   2.750   0.4831   0.00773   0.00178  -0.0339   0.3109   1.0000
   3.000   0.5101   0.00793   0.00190  -0.0337   0.2915   1.0000
   3.250   0.5371   0.00813   0.00202  -0.0335   0.2723   1.0000
   3.500   0.5642   0.00834   0.00216  -0.0333   0.2553   1.0000
   3.750   0.5911   0.00856   0.00231  -0.0331   0.2370   1.0000
   4.000   0.6180   0.00879   0.00248  -0.0329   0.2206   1.0000
   4.250   0.6449   0.00904   0.00265  -0.0327   0.2043   1.0000
   4.500   0.6717   0.00928   0.00285  -0.0325   0.1888   1.0000
   4.750   0.6984   0.00954   0.00305  -0.0323   0.1739   1.0000
   5.000   0.7251   0.00980   0.00327  -0.0321   0.1599   1.0000
   5.250   0.7517   0.01008   0.00350  -0.0319   0.1463   1.0000
   5.500   0.7782   0.01037   0.00376  -0.0317   0.1339   1.0000
   5.750   0.8047   0.01065   0.00402  -0.0315   0.1234   1.0000
   6.000   0.8311   0.01095   0.00429  -0.0312   0.1127   1.0000
   6.250   0.8572   0.01128   0.00459  -0.0310   0.1014   1.0000
   6.500   0.8830   0.01166   0.00493  -0.0307   0.0882   1.0000
   6.750   0.9087   0.01205   0.00527  -0.0304   0.0763   1.0000
   7.000   0.9343   0.01243   0.00563  -0.0301   0.0672   1.0000
   7.250   0.9597   0.01284   0.00601  -0.0298   0.0591   1.0000
   7.500   0.9853   0.01321   0.00642  -0.0295   0.0526   1.0000
   7.750   1.0103   0.01366   0.00685  -0.0291   0.0460   1.0000
   8.000   1.0352   0.01412   0.00731  -0.0287   0.0396   1.0000
   8.250   1.0599   0.01460   0.00780  -0.0283   0.0337   1.0000
   8.500   1.0840   0.01515   0.00835  -0.0279   0.0280   1.0000
   8.750   1.1079   0.01571   0.00894  -0.0274   0.0236   1.0000
   9.000   1.1316   0.01628   0.00955  -0.0269   0.0205   1.0000
   9.250   1.1548   0.01690   0.01022  -0.0263   0.0182   1.0000
   9.500   1.1774   0.01760   0.01097  -0.0257   0.0165   1.0000
   9.750   1.2002   0.01822   0.01168  -0.0251   0.0155   1.0000
  10.000   1.2224   0.01889   0.01244  -0.0244   0.0144   1.0000
  10.250   1.2438   0.01965   0.01326  -0.0237   0.0135   1.0000
  10.500   1.2634   0.02059   0.01429  -0.0228   0.0127   1.0000
  10.750   1.2831   0.02146   0.01526  -0.0219   0.0122   1.0000
  11.000   1.3029   0.02227   0.01618  -0.0211   0.0117   1.0000
  11.250   1.3215   0.02314   0.01717  -0.0201   0.0113   1.0000
  11.500   1.3393   0.02406   0.01820  -0.0191   0.0108   1.0000
  11.750   1.3561   0.02500   0.01924  -0.0180   0.0103   1.0000
  12.000   1.3706   0.02609   0.02043  -0.0167   0.0099   1.0000
  12.250   1.3820   0.02736   0.02180  -0.0152   0.0095   1.0000
  12.500   1.3866   0.02896   0.02352  -0.0129   0.0092   1.0000
  12.750   1.3899   0.03030   0.02498  -0.0104   0.0090   1.0000
  13.000   1.3936   0.03165   0.02646  -0.0083   0.0088   1.0000
  13.250   1.3952   0.03327   0.02822  -0.0065   0.0086   1.0000
  13.500   1.3955   0.03521   0.03029  -0.0054   0.0083   1.0000
  13.750   1.3934   0.03766   0.03288  -0.0048   0.0081   1.0000
  14.000   1.3885   0.04075   0.03614  -0.0051   0.0080   1.0000
  14.250   1.3825   0.04444   0.03998  -0.0063   0.0079   1.0000
  14.500   1.3741   0.04888   0.04457  -0.0083   0.0077   1.0000
  14.750   1.3639   0.05403   0.04988  -0.0110   0.0077   1.0000
  15.000   1.3506   0.06003   0.05604  -0.0145   0.0076   1.0000
  15.250   1.3357   0.06658   0.06274  -0.0183   0.0075   1.0000
  15.500   1.3177   0.07386   0.07017  -0.0225   0.0075   1.0000
  15.750   1.2957   0.08202   0.07848  -0.0272   0.0076   1.0000
  16.000   1.2734   0.09044   0.08705  -0.0320   0.0076   1.0000
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