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SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD7032-099-88 (sd7032-il)
Reynolds number: 200,000
Max Cl/Cd: 77.87 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7032-il-200000.txt
Download as CSV file: xf-sd7032-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2585   0.09769   0.09447  -0.0394   1.0000   0.0407
  -9.250  -0.2669   0.09516   0.09201  -0.0400   1.0000   0.0409
  -9.000  -0.2754   0.09273   0.08964  -0.0395   1.0000   0.0410
  -8.750  -0.2707   0.08793   0.08488  -0.0362   1.0000   0.0423
  -8.500  -0.2656   0.08626   0.08324  -0.0329   1.0000   0.0441
  -8.250  -0.2719   0.08433   0.08135  -0.0310   1.0000   0.0449
  -8.000  -0.2804   0.08243   0.07950  -0.0290   1.0000   0.0459
  -7.750  -0.2906   0.08053   0.07766  -0.0272   1.0000   0.0467
  -7.500  -0.3027   0.07864   0.07584  -0.0253   1.0000   0.0475
  -7.250  -0.3805   0.08449   0.08152  -0.0263   1.0000   0.0441
  -7.000  -0.3980   0.08316   0.08027  -0.0236   1.0000   0.0442
  -6.750  -0.4039   0.08084   0.07799  -0.0237   0.9994   0.0448
  -6.500  -0.3750   0.07508   0.07220  -0.0340   0.9936   0.0483
  -6.250  -0.3258   0.06369   0.06028  -0.0632   0.9832   0.0524
  -6.000  -0.3146   0.05790   0.05470  -0.0634   0.9782   0.0542
  -5.750  -0.2875   0.05513   0.05192  -0.0658   0.9738   0.0565
  -5.250  -0.2227   0.04381   0.03997  -0.0803   0.9612   0.0677
  -5.000  -0.1870   0.04081   0.03691  -0.0840   0.9581   0.0721
  -4.750  -0.1574   0.03666   0.03233  -0.0877   0.9505   0.0818
  -4.500  -0.1135   0.02580   0.01995  -0.0905   0.9467   0.0390
  -4.250  -0.0709   0.02331   0.01692  -0.0933   0.9440   0.0401
  -4.000  -0.0377   0.02090   0.01411  -0.0943   0.9382   0.0398
  -3.750   0.0006   0.01934   0.01221  -0.0958   0.9335   0.0408
  -3.500   0.0403   0.01744   0.01027  -0.0982   0.9304   0.0457
  -3.250   0.0757   0.01644   0.00918  -0.0993   0.9252   0.0498
  -3.000   0.1075   0.01538   0.00810  -0.0998   0.9182   0.0558
  -2.750   0.1455   0.01462   0.00730  -0.1014   0.9142   0.0651
  -2.500   0.1724   0.01379   0.00659  -0.1010   0.9049   0.0849
  -2.250   0.2049   0.01229   0.00591  -0.1022   0.8996   0.2794
  -2.000   0.2292   0.01154   0.00578  -0.1015   0.8898   0.4551
  -1.750   0.2573   0.01087   0.00563  -0.1009   0.8840   0.6181
  -1.500   0.2763   0.01050   0.00563  -0.0981   0.8730   0.7441
  -1.250   0.2960   0.01022   0.00550  -0.0953   0.8635   0.8273
  -1.000   0.3188   0.00990   0.00522  -0.0929   0.8555   0.8971
  -0.750   0.3651   0.00957   0.00484  -0.0959   0.8456   0.9915
  -0.500   0.3938   0.00949   0.00459  -0.0959   0.8349   1.0000
  -0.250   0.4217   0.00941   0.00435  -0.0955   0.8243   1.0000
   0.000   0.4487   0.00937   0.00417  -0.0951   0.8120   1.0000
   0.250   0.4756   0.00935   0.00403  -0.0947   0.7988   1.0000
   0.500   0.5026   0.00936   0.00391  -0.0942   0.7852   1.0000
   0.750   0.5297   0.00937   0.00381  -0.0938   0.7713   1.0000
   1.000   0.5569   0.00941   0.00372  -0.0934   0.7567   1.0000
   1.250   0.5839   0.00947   0.00367  -0.0930   0.7416   1.0000
   1.500   0.6110   0.00954   0.00363  -0.0926   0.7262   1.0000
   1.750   0.6379   0.00964   0.00361  -0.0922   0.7102   1.0000
   2.000   0.6647   0.00976   0.00362  -0.0918   0.6939   1.0000
   2.250   0.6912   0.00990   0.00367  -0.0913   0.6761   1.0000
   2.500   0.7176   0.01005   0.00373  -0.0909   0.6581   1.0000
   2.750   0.7439   0.01023   0.00381  -0.0904   0.6401   1.0000
   3.000   0.7700   0.01042   0.00389  -0.0900   0.6221   1.0000
   3.250   0.7960   0.01063   0.00401  -0.0895   0.6033   1.0000
   3.500   0.8218   0.01084   0.00417  -0.0890   0.5844   1.0000
   3.750   0.8474   0.01108   0.00432  -0.0885   0.5659   1.0000
   4.000   0.8730   0.01135   0.00449  -0.0881   0.5480   1.0000
   4.250   0.8983   0.01160   0.00469  -0.0876   0.5291   1.0000
   4.500   0.9235   0.01188   0.00493  -0.0871   0.5105   1.0000
   4.750   0.9485   0.01218   0.00516  -0.0865   0.4925   1.0000
   5.000   0.9734   0.01251   0.00541  -0.0860   0.4750   1.0000
   5.250   0.9980   0.01283   0.00569  -0.0854   0.4570   1.0000
   5.500   1.0225   0.01316   0.00602  -0.0849   0.4391   1.0000
   5.750   1.0467   0.01351   0.00634  -0.0843   0.4215   1.0000
   6.000   1.0705   0.01389   0.00667  -0.0836   0.4042   1.0000
   6.250   1.0941   0.01430   0.00703  -0.0830   0.3873   1.0000
   6.500   1.1174   0.01470   0.00742  -0.0823   0.3697   1.0000
   6.750   1.1404   0.01510   0.00782  -0.0815   0.3521   1.0000
   7.000   1.1631   0.01553   0.00824  -0.0808   0.3349   1.0000
   7.250   1.1851   0.01599   0.00870  -0.0799   0.3177   1.0000
   7.500   1.2066   0.01649   0.00916  -0.0790   0.3009   1.0000
   7.750   1.2277   0.01701   0.00966  -0.0781   0.2844   1.0000
   8.000   1.2487   0.01751   0.01018  -0.0771   0.2675   1.0000
   8.250   1.2691   0.01804   0.01075  -0.0761   0.2513   1.0000
   8.500   1.2888   0.01861   0.01134  -0.0750   0.2355   1.0000
   8.750   1.3077   0.01922   0.01196  -0.0737   0.2199   1.0000
   9.000   1.3257   0.01986   0.01262  -0.0724   0.2042   1.0000
   9.250   1.3425   0.02056   0.01332  -0.0710   0.1889   1.0000
   9.500   1.3577   0.02134   0.01410  -0.0693   0.1734   1.0000
   9.750   1.3708   0.02222   0.01496  -0.0674   0.1580   1.0000
  10.000   1.3823   0.02309   0.01584  -0.0652   0.1426   1.0000
  10.250   1.3917   0.02407   0.01684  -0.0628   0.1278   1.0000
  10.500   1.3994   0.02519   0.01796  -0.0603   0.1144   1.0000
  10.750   1.4052   0.02649   0.01923  -0.0577   0.1028   1.0000
  11.000   1.4101   0.02791   0.02064  -0.0553   0.0929   1.0000
  11.250   1.4172   0.02926   0.02209  -0.0532   0.0840   1.0000
  11.500   1.4199   0.03101   0.02387  -0.0509   0.0774   1.0000
  11.750   1.4246   0.03262   0.02557  -0.0491   0.0711   1.0000
  12.000   1.4260   0.03467   0.02766  -0.0471   0.0660   1.0000
  12.250   1.4305   0.03646   0.02957  -0.0456   0.0608   1.0000
  12.500   1.4280   0.03906   0.03214  -0.0440   0.0564   1.0000
  12.750   1.4327   0.04096   0.03426  -0.0430   0.0520   1.0000
  13.000   1.4321   0.04346   0.03681  -0.0420   0.0482   1.0000
  13.250   1.4298   0.04639   0.03983  -0.0411   0.0448   1.0000
  13.500   1.4305   0.04902   0.04264  -0.0407   0.0413   1.0000
  13.750   1.4274   0.05215   0.04584  -0.0406   0.0385   1.0000
  14.000   1.4218   0.05584   0.04959  -0.0402   0.0358   1.0000
  14.250   1.4194   0.05925   0.05325  -0.0405   0.0334   1.0000
  14.500   1.4153   0.06296   0.05707  -0.0413   0.0310   1.0000
  14.750   1.4087   0.06711   0.06125  -0.0420   0.0291   1.0000
  15.000   1.4016   0.07158   0.06588  -0.0428   0.0272   1.0000
  15.250   1.3957   0.07612   0.07063  -0.0441   0.0256   1.0000
  15.500   1.3899   0.08073   0.07538  -0.0457   0.0242   1.0000
  15.750   1.3839   0.08541   0.08016  -0.0473   0.0230   1.0000
  16.000   1.3772   0.09020   0.08500  -0.0487   0.0219   1.0000
  16.250   1.3686   0.09555   0.09051  -0.0502   0.0210   1.0000
  16.500   1.3595   0.10134   0.09653  -0.0528   0.0205   1.0000
  16.750   1.3497   0.10740   0.10280  -0.0557   0.0200   1.0000
  17.000   1.3394   0.11370   0.10930  -0.0589   0.0194   1.0000
  17.250   1.3286   0.12026   0.11605  -0.0624   0.0190   1.0000
  17.500   1.3170   0.12714   0.12312  -0.0664   0.0186   1.0000
  17.750   1.3048   0.13439   0.13055  -0.0707   0.0184   1.0000
  18.000   1.2920   0.14198   0.13832  -0.0755   0.0181   1.0000
  18.250   1.2753   0.15082   0.14736  -0.0812   0.0182   1.0000
  18.500   1.2530   0.16159   0.15835  -0.0884   0.0186   1.0000
  18.750   1.2200   0.17616   0.17314  -0.0982   0.0197   1.0000
  19.000   1.1860   0.19231   0.18942  -0.1089   0.0208   1.0000
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