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AG38 (ag38-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AG38 (ag38-il)
Reynolds number: 50,000
Max Cl/Cd: 36.03 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag38-il-50000-n5.txt
Download as CSV file: xf-ag38-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG38                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5184   0.10746   0.10044  -0.0006   1.0000   0.1082
  -9.250  -0.5323   0.10548   0.09860  -0.0065   1.0000   0.1122
  -9.000  -0.5317   0.10146   0.09467  -0.0102   1.0000   0.1132
  -8.750  -0.5183   0.09687   0.09009  -0.0075   1.0000   0.1151
  -8.500  -0.5105   0.09303   0.08628  -0.0083   1.0000   0.1172
  -8.000  -0.4915   0.07819   0.07119  -0.0258   1.0000   0.0564
  -7.750  -0.4817   0.07415   0.06715  -0.0263   1.0000   0.0552
  -7.500  -0.4709   0.06974   0.06269  -0.0284   1.0000   0.0543
  -7.250  -0.4585   0.06523   0.05808  -0.0307   1.0000   0.0536
  -7.000  -0.4443   0.06071   0.05341  -0.0329   1.0000   0.0528
  -6.750  -0.4282   0.05617   0.04867  -0.0349   1.0000   0.0516
  -6.500  -0.4101   0.05156   0.04377  -0.0366   1.0000   0.0499
  -6.250  -0.3897   0.04695   0.03876  -0.0381   1.0000   0.0483
  -6.000  -0.3676   0.04270   0.03401  -0.0391   1.0000   0.0472
  -5.750  -0.3443   0.03901   0.02978  -0.0394   1.0000   0.0466
  -5.500  -0.3206   0.03591   0.02622  -0.0394   1.0000   0.0469
  -5.250  -0.2971   0.03357   0.02358  -0.0392   1.0000   0.0493
  -5.000  -0.2723   0.03131   0.02090  -0.0388   1.0000   0.0523
  -4.750  -0.2464   0.02908   0.01820  -0.0382   1.0000   0.0541
  -4.500  -0.2204   0.02709   0.01578  -0.0374   1.0000   0.0556
  -4.250  -0.1950   0.02533   0.01374  -0.0365   1.0000   0.0585
  -4.000  -0.1705   0.02404   0.01238  -0.0358   1.0000   0.0650
  -3.750  -0.1446   0.02281   0.01087  -0.0348   1.0000   0.0703
  -3.500  -0.1198   0.02165   0.00970  -0.0340   1.0000   0.0786
  -3.250  -0.0942   0.02069   0.00867  -0.0334   1.0000   0.0929
  -3.000  -0.0684   0.01970   0.00770  -0.0329   1.0000   0.1182
  -2.750  -0.0420   0.01799   0.00685  -0.0332   1.0000   0.2520
  -2.500  -0.0178   0.01532   0.00648  -0.0308   1.0000   1.0000
  -2.250   0.0059   0.01537   0.00612  -0.0300   1.0000   1.0000
  -2.000   0.0294   0.01544   0.00586  -0.0293   1.0000   1.0000
  -1.750   0.0529   0.01554   0.00571  -0.0287   1.0000   1.0000
  -1.500   0.0763   0.01568   0.00564  -0.0281   1.0000   1.0000
  -1.250   0.0995   0.01584   0.00564  -0.0276   1.0000   1.0000
  -1.000   0.1226   0.01605   0.00570  -0.0272   1.0000   1.0000
  -0.750   0.1452   0.01630   0.00584  -0.0268   1.0000   1.0000
  -0.500   0.1677   0.01661   0.00608  -0.0265   0.9998   1.0000
  -0.250   0.2177   0.01687   0.00624  -0.0315   0.9811   1.0000
   0.000   0.2657   0.01705   0.00638  -0.0359   0.9602   1.0000
   0.250   0.3129   0.01716   0.00650  -0.0400   0.9382   1.0000
   0.500   0.3571   0.01720   0.00656  -0.0431   0.9132   1.0000
   0.750   0.3936   0.01722   0.00661  -0.0446   0.8811   1.0000
   1.000   0.4328   0.01717   0.00659  -0.0462   0.8509   1.0000
   1.250   0.4710   0.01715   0.00659  -0.0474   0.8199   1.0000
   1.500   0.5051   0.01721   0.00661  -0.0477   0.7870   1.0000
   1.750   0.5344   0.01739   0.00675  -0.0473   0.7517   1.0000
   2.000   0.5615   0.01764   0.00698  -0.0464   0.7165   1.0000
   2.250   0.5871   0.01793   0.00722  -0.0454   0.6807   1.0000
   2.500   0.6121   0.01824   0.00747  -0.0442   0.6457   1.0000
   2.750   0.6369   0.01860   0.00771  -0.0430   0.6130   1.0000
   3.000   0.6612   0.01905   0.00810  -0.0418   0.5792   1.0000
   3.250   0.6853   0.01954   0.00859  -0.0408   0.5452   1.0000
   3.500   0.7091   0.02005   0.00907  -0.0397   0.5103   1.0000
   3.750   0.7328   0.02056   0.00960  -0.0388   0.4720   1.0000
   4.000   0.7560   0.02106   0.01012  -0.0378   0.4305   1.0000
   4.250   0.7785   0.02161   0.01066  -0.0367   0.3868   1.0000
   4.500   0.8005   0.02228   0.01121  -0.0357   0.3415   1.0000
   4.750   0.8222   0.02312   0.01191  -0.0348   0.2957   1.0000
   5.000   0.8436   0.02410   0.01277  -0.0340   0.2509   1.0000
   5.250   0.8646   0.02524   0.01381  -0.0332   0.2106   1.0000
   5.500   0.8854   0.02651   0.01502  -0.0325   0.1754   1.0000
   5.750   0.9059   0.02792   0.01638  -0.0317   0.1483   1.0000
   6.000   0.9257   0.02941   0.01780  -0.0309   0.1272   1.0000
   6.250   0.9462   0.03099   0.01948  -0.0299   0.1114   1.0000
   6.500   0.9664   0.03266   0.02125  -0.0290   0.0996   1.0000
   6.750   0.9855   0.03432   0.02293  -0.0282   0.0893   1.0000
   7.000   1.0072   0.03636   0.02533  -0.0272   0.0820   1.0000
   7.250   1.0266   0.03835   0.02730  -0.0264   0.0761   1.0000
   7.500   1.0452   0.04061   0.03006  -0.0254   0.0696   1.0000
   7.750   1.0632   0.04291   0.03257  -0.0245   0.0657   1.0000
   8.000   1.0796   0.04598   0.03593  -0.0236   0.0631   1.0000
   8.250   1.0901   0.04947   0.04005  -0.0222   0.0602   1.0000
   8.500   1.0983   0.05262   0.04363  -0.0209   0.0569   1.0000
   8.750   1.1061   0.05547   0.04672  -0.0198   0.0543   1.0000
   9.000   1.1116   0.05889   0.05037  -0.0186   0.0529   1.0000
   9.250   1.1098   0.06310   0.05487  -0.0174   0.0521   1.0000
   9.500   1.0978   0.06770   0.05989  -0.0160   0.0518   1.0000
   9.750   1.0802   0.07218   0.06467  -0.0148   0.0517   1.0000
  10.000   1.0593   0.07701   0.06973  -0.0147   0.0517   1.0000
  10.250   1.0373   0.08275   0.07564  -0.0167   0.0519   1.0000
  10.500   1.0155   0.08956   0.08259  -0.0206   0.0521   1.0000
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