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

SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD7032-099-88 (sd7032-il)
Reynolds number: 500,000
Max Cl/Cd: 105.45 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7032-il-500000.txt
Download as CSV file: xf-sd7032-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7032-099-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3212   0.09126   0.08908  -0.0369   1.0000   0.0173
  -8.500  -0.3335   0.08817   0.08605  -0.0369   1.0000   0.0179
  -8.250  -0.3494   0.08653   0.08448  -0.0341   1.0000   0.0180
  -8.000  -0.3370   0.08125   0.07921  -0.0405   0.9968   0.0181
  -7.750  -0.3212   0.07552   0.07348  -0.0482   0.9917   0.0182
  -7.500  -0.3090   0.06625   0.06423  -0.0608   0.9853   0.0186
  -7.250  -0.2860   0.06332   0.06129  -0.0657   0.9827   0.0193
  -7.000  -0.2616   0.05743   0.05535  -0.0758   0.9767   0.0198
  -6.750  -0.2308   0.05001   0.04781  -0.0879   0.9729   0.0205
  -6.500  -0.2060   0.04270   0.04025  -0.0962   0.9658   0.0222
  -6.250  -0.1774   0.03651   0.03342  -0.1018   0.9585   0.0240
  -6.000  -0.1686   0.02987   0.02650  -0.1036   0.9490   0.0252
  -5.750  -0.1448   0.02890   0.02552  -0.1040   0.9437   0.0265
  -5.500  -0.1288   0.02015   0.01559  -0.1027   0.9338   0.0176
  -5.250  -0.1055   0.01737   0.01240  -0.1021   0.9283   0.0170
  -5.000  -0.0816   0.01570   0.01042  -0.1013   0.9206   0.0174
  -4.750  -0.0556   0.01481   0.00928  -0.1006   0.9147   0.0180
  -4.500  -0.0313   0.01307   0.00735  -0.0999   0.9075   0.0189
  -4.250  -0.0058   0.01229   0.00653  -0.0993   0.9008   0.0203
  -4.000   0.0206   0.01190   0.00610  -0.0989   0.8936   0.0224
  -3.750   0.0473   0.01147   0.00556  -0.0983   0.8863   0.0239
  -3.500   0.0729   0.01041   0.00444  -0.0979   0.8784   0.0263
  -3.250   0.0998   0.01001   0.00399  -0.0975   0.8708   0.0292
  -3.000   0.1269   0.00965   0.00356  -0.0971   0.8620   0.0324
  -2.750   0.1541   0.00921   0.00307  -0.0968   0.8540   0.0372
  -2.500   0.1815   0.00891   0.00273  -0.0966   0.8441   0.0445
  -2.250   0.2089   0.00842   0.00239  -0.0964   0.8345   0.0904
  -2.000   0.2358   0.00792   0.00220  -0.0963   0.8248   0.1949
  -1.750   0.2629   0.00753   0.00208  -0.0963   0.8136   0.2885
  -1.500   0.2900   0.00718   0.00198  -0.0962   0.8020   0.3911
  -1.250   0.3166   0.00679   0.00195  -0.0960   0.7902   0.5201
  -1.000   0.3429   0.00652   0.00193  -0.0956   0.7778   0.6233
  -0.750   0.3686   0.00634   0.00193  -0.0949   0.7648   0.7079
  -0.500   0.3938   0.00622   0.00193  -0.0940   0.7514   0.7746
  -0.250   0.4180   0.00614   0.00193  -0.0929   0.7372   0.8308
   0.000   0.4406   0.00607   0.00191  -0.0913   0.7229   0.8851
   0.250   0.4649   0.00599   0.00185  -0.0900   0.7081   0.9426
   0.500   0.5020   0.00601   0.00178  -0.0919   0.6921   1.0000
   0.750   0.5296   0.00612   0.00177  -0.0918   0.6760   1.0000
   1.000   0.5571   0.00624   0.00178  -0.0917   0.6596   1.0000
   1.250   0.5844   0.00637   0.00180  -0.0916   0.6429   1.0000
   1.500   0.6117   0.00651   0.00184  -0.0914   0.6258   1.0000
   1.750   0.6387   0.00667   0.00188  -0.0912   0.6084   1.0000
   2.000   0.6657   0.00683   0.00194  -0.0910   0.5908   1.0000
   2.250   0.6927   0.00699   0.00201  -0.0908   0.5726   1.0000
   2.500   0.7196   0.00716   0.00209  -0.0906   0.5549   1.0000
   2.750   0.7464   0.00734   0.00219  -0.0904   0.5372   1.0000
   3.000   0.7730   0.00754   0.00229  -0.0902   0.5198   1.0000
   3.250   0.7995   0.00774   0.00241  -0.0900   0.5028   1.0000
   3.500   0.8261   0.00793   0.00255  -0.0898   0.4853   1.0000
   3.750   0.8526   0.00814   0.00269  -0.0895   0.4684   1.0000
   4.000   0.8789   0.00836   0.00283  -0.0893   0.4515   1.0000
   4.250   0.9051   0.00859   0.00300  -0.0890   0.4345   1.0000
   4.500   0.9311   0.00883   0.00318  -0.0888   0.4184   1.0000
   4.750   0.9570   0.00908   0.00337  -0.0885   0.4021   1.0000
   5.000   0.9827   0.00934   0.00357  -0.0881   0.3859   1.0000
   5.250   1.0084   0.00960   0.00379  -0.0878   0.3697   1.0000
   5.500   1.0339   0.00987   0.00402  -0.0875   0.3532   1.0000
   5.750   1.0592   0.01015   0.00425  -0.0872   0.3370   1.0000
   6.000   1.0844   0.01045   0.00450  -0.0868   0.3210   1.0000
   6.250   1.1092   0.01076   0.00478  -0.0864   0.3049   1.0000
   6.500   1.1337   0.01110   0.00506  -0.0859   0.2883   1.0000
   6.750   1.1579   0.01146   0.00537  -0.0854   0.2718   1.0000
   7.000   1.1819   0.01183   0.00569  -0.0849   0.2559   1.0000
   7.250   1.2058   0.01220   0.00603  -0.0844   0.2412   1.0000
   7.500   1.2295   0.01258   0.00638  -0.0838   0.2264   1.0000
   7.750   1.2528   0.01298   0.00675  -0.0832   0.2111   1.0000
   8.000   1.2757   0.01341   0.00715  -0.0826   0.1969   1.0000
   8.250   1.2981   0.01386   0.00758  -0.0819   0.1823   1.0000
   8.500   1.3201   0.01433   0.00802  -0.0811   0.1681   1.0000
   8.750   1.3415   0.01484   0.00850  -0.0802   0.1541   1.0000
   9.000   1.3622   0.01537   0.00900  -0.0793   0.1396   1.0000
   9.250   1.3823   0.01595   0.00955  -0.0783   0.1250   1.0000
   9.500   1.4011   0.01659   0.01014  -0.0771   0.1097   1.0000
   9.750   1.4185   0.01731   0.01080  -0.0757   0.0948   1.0000
  10.000   1.4345   0.01810   0.01152  -0.0742   0.0812   1.0000
  10.250   1.4493   0.01889   0.01228  -0.0724   0.0699   1.0000
  10.500   1.4622   0.01965   0.01303  -0.0703   0.0608   1.0000
  10.750   1.4740   0.02043   0.01383  -0.0681   0.0535   1.0000
  11.000   1.4832   0.02137   0.01475  -0.0656   0.0472   1.0000
  11.250   1.4956   0.02213   0.01558  -0.0636   0.0430   1.0000
  11.500   1.5044   0.02314   0.01660  -0.0614   0.0386   1.0000
  11.750   1.5137   0.02416   0.01769  -0.0593   0.0353   1.0000
  12.000   1.5238   0.02514   0.01874  -0.0574   0.0321   1.0000
  12.250   1.5275   0.02663   0.02025  -0.0550   0.0285   1.0000
  12.500   1.5382   0.02766   0.02138  -0.0535   0.0261   1.0000
  12.750   1.5443   0.02907   0.02284  -0.0518   0.0231   1.0000
  13.000   1.5474   0.03080   0.02465  -0.0499   0.0205   1.0000
  13.250   1.5537   0.03234   0.02625  -0.0486   0.0179   1.0000
  13.500   1.5509   0.03478   0.02875  -0.0469   0.0157   1.0000
  13.750   1.5546   0.03673   0.03081  -0.0458   0.0139   1.0000
  14.000   1.5503   0.03959   0.03373  -0.0447   0.0122   1.0000
  14.250   1.5453   0.04271   0.03698  -0.0439   0.0111   1.0000
  14.500   1.5428   0.04573   0.04014  -0.0436   0.0103   1.0000
  14.750   1.5387   0.04910   0.04362  -0.0436   0.0096   1.0000
  15.000   1.5284   0.05345   0.04808  -0.0440   0.0089   1.0000
  15.250   1.5127   0.05886   0.05364  -0.0451   0.0085   1.0000
  15.500   1.5032   0.06369   0.05862  -0.0464   0.0083   1.0000
  15.750   1.4962   0.06837   0.06345  -0.0478   0.0080   1.0000
  16.000   1.4863   0.07369   0.06891  -0.0497   0.0077   1.0000
  16.250   1.4750   0.07941   0.07479  -0.0519   0.0076   1.0000
  16.500   1.4632   0.08543   0.08095  -0.0544   0.0074   1.0000
  16.750   1.4507   0.09174   0.08739  -0.0571   0.0072   1.0000
  17.000   1.4382   0.09821   0.09399  -0.0601   0.0071   1.0000
  17.250   1.4251   0.10493   0.10085  -0.0633   0.0070   1.0000
<< Back to SD7032-099-88 (sd7032-il)

Polar data table (+)

Polar graphs


<< Back to SD7032-099-88 (sd7032-il)