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DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il)
Reynolds number: 100,000
Max Cl/Cd: 33.64 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dfvlrr4-il-100000.txt
Download as CSV file: xf-dfvlrr4-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DFVLR R-4 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5545   0.10573   0.10053  -0.0442   1.0000   0.1683
 -10.500  -0.5650   0.06804   0.06309  -0.0586   1.0000   0.0882
 -10.250  -0.6084   0.06225   0.05726  -0.0580   1.0000   0.0863
 -10.000  -0.6537   0.05827   0.05322  -0.0552   1.0000   0.0850
  -9.750  -0.7605   0.06716   0.06170  -0.0519   1.0000   0.0894
  -9.500  -0.8058   0.06053   0.05444  -0.0492   1.0000   0.0781
  -9.250  -0.8069   0.05646   0.05024  -0.0476   1.0000   0.0760
  -9.000  -0.8108   0.05194   0.04535  -0.0463   1.0000   0.0732
  -8.750  -0.8143   0.04631   0.03864  -0.0453   1.0000   0.0690
  -8.500  -0.8006   0.04324   0.03535  -0.0447   1.0000   0.0697
  -8.250  -0.7839   0.04118   0.03327  -0.0439   1.0000   0.0716
  -8.000  -0.7663   0.03885   0.03067  -0.0434   1.0000   0.0730
  -7.750  -0.7465   0.03643   0.02792  -0.0429   1.0000   0.0739
  -7.500  -0.7251   0.03427   0.02544  -0.0423   1.0000   0.0752
  -7.250  -0.7026   0.03246   0.02331  -0.0418   1.0000   0.0774
  -7.000  -0.6794   0.03073   0.02133  -0.0413   1.0000   0.0811
  -6.750  -0.6572   0.02932   0.01997  -0.0407   1.0000   0.0857
  -6.500  -0.6337   0.02811   0.01862  -0.0399   1.0000   0.0908
  -6.250  -0.6115   0.02671   0.01733  -0.0390   1.0000   0.0978
  -6.000  -0.5880   0.02568   0.01625  -0.0384   1.0000   0.1081
  -5.750  -0.5643   0.02470   0.01536  -0.0380   1.0000   0.1209
  -5.500  -0.5398   0.02351   0.01442  -0.0381   1.0000   0.1399
  -5.250  -0.5111   0.02225   0.01347  -0.0394   1.0000   0.1722
  -5.000  -0.4644   0.01920   0.01286  -0.0458   1.0000   0.5129
  -4.750  -0.4489   0.02014   0.01391  -0.0420   1.0000   0.5875
  -4.500  -0.4330   0.02114   0.01483  -0.0385   1.0000   0.6193
  -4.250  -0.4221   0.02229   0.01594  -0.0337   1.0000   0.6377
  -4.000  -0.4099   0.02337   0.01696  -0.0292   1.0000   0.6537
  -3.750  -0.3965   0.02435   0.01787  -0.0252   1.0000   0.6687
  -3.500  -0.3828   0.02526   0.01871  -0.0214   1.0000   0.6833
  -3.250  -0.3706   0.02619   0.01958  -0.0172   1.0000   0.6981
  -3.000  -0.3596   0.02706   0.02041  -0.0126   1.0000   0.7131
  -2.750  -0.3542   0.02784   0.02120  -0.0065   1.0000   0.7246
  -2.500  -0.3445   0.02840   0.02173  -0.0018   1.0000   0.7385
  -2.250  -0.3327   0.02875   0.02203   0.0021   1.0000   0.7526
  -2.000  -0.3174   0.02889   0.02212   0.0048   1.0000   0.7660
  -1.750  -0.2957   0.02887   0.02202   0.0053   1.0000   0.7783
  -1.500  -0.2773   0.02874   0.02184   0.0067   1.0000   0.7867
  -1.250  -0.2530   0.02858   0.02161   0.0062   1.0000   0.7954
  -1.000  -0.2304   0.02850   0.02148   0.0063   1.0000   0.8045
  -0.750  -0.2112   0.02836   0.02130   0.0073   1.0000   0.8129
  -0.500  -0.1832   0.02841   0.02129   0.0058   1.0000   0.8228
  -0.250  -0.1682   0.02822   0.02109   0.0079   1.0000   0.8305
   0.000  -0.1409   0.02828   0.02112   0.0065   1.0000   0.8389
   0.250  -0.1222   0.02820   0.02103   0.0074   1.0000   0.8463
   0.500  -0.0969   0.02830   0.02112   0.0065   1.0000   0.8541
   0.750  -0.0563   0.02862   0.02143   0.0032   0.9917   0.8618
   1.000  -0.0108   0.02901   0.02181  -0.0013   0.9817   0.8690
   1.250   0.0319   0.02933   0.02213  -0.0049   0.9721   0.8756
   1.500   0.0751   0.02957   0.02239  -0.0089   0.9607   0.8820
   1.750   0.1074   0.02952   0.02238  -0.0102   0.9486   0.8883
   2.000   0.1489   0.02969   0.02260  -0.0137   0.9365   0.8943
   2.250   0.1903   0.02955   0.02251  -0.0163   0.9220   0.8997
   2.500   0.2462   0.02890   0.02192  -0.0205   0.9009   0.9058
   2.750   0.3079   0.02767   0.02076  -0.0248   0.8778   0.9112
   3.000   0.3489   0.02650   0.01968  -0.0257   0.8591   0.9168
   3.250   0.3935   0.02546   0.01875  -0.0276   0.8439   0.9221
   3.500   0.4361   0.02425   0.01767  -0.0288   0.8299   0.9271
   3.750   0.4750   0.02292   0.01647  -0.0291   0.8132   0.9318
   4.000   0.5184   0.02125   0.01494  -0.0297   0.7921   0.9359
   4.250   0.5528   0.01966   0.01347  -0.0287   0.7609   0.9404
   4.500   0.5786   0.01837   0.01225  -0.0264   0.7059   0.9461
   4.750   0.6189   0.01840   0.01044  -0.0253   0.3854   0.9494
   5.000   0.6264   0.01985   0.01096  -0.0223   0.2759   0.9538
   5.250   0.6466   0.02076   0.01152  -0.0215   0.2372   0.9584
   5.500   0.6708   0.02155   0.01210  -0.0214   0.2155   0.9631
   5.750   0.6995   0.02229   0.01273  -0.0220   0.2008   0.9675
   6.000   0.7316   0.02319   0.01354  -0.0232   0.1899   0.9716
   6.250   0.7665   0.02422   0.01442  -0.0251   0.1809   0.9759
   6.500   0.8020   0.02517   0.01550  -0.0269   0.1731   0.9805
   7.000   0.8750   0.02753   0.01791  -0.0313   0.1590   0.9897
   7.250   0.9077   0.02858   0.01911  -0.0327   0.1530   0.9985
   7.500   0.9415   0.03035   0.02080  -0.0346   0.1483   1.0000
   7.750   0.9665   0.03158   0.02238  -0.0347   0.1436   1.0000
   8.000   0.9934   0.03278   0.02376  -0.0353   0.1377   1.0000
   8.250   1.0248   0.03494   0.02584  -0.0371   0.1324   1.0000
   8.500   1.0466   0.03663   0.02802  -0.0366   0.1291   1.0000
   8.750   1.0692   0.03872   0.03052  -0.0365   0.1255   1.0000
   9.000   1.0931   0.04091   0.03299  -0.0368   0.1221   1.0000
   9.250   1.1203   0.04330   0.03540  -0.0379   0.1186   1.0000
   9.500   1.1335   0.04661   0.03916  -0.0369   0.1157   1.0000
   9.750   1.1397   0.04967   0.04282  -0.0349   0.1130   1.0000
  10.000   1.1450   0.05301   0.04662  -0.0331   0.1104   1.0000
  10.250   1.1542   0.05584   0.04973  -0.0320   0.1074   1.0000
  10.500   1.1885   0.05847   0.05209  -0.0346   0.1031   1.0000
  10.750   1.1771   0.06275   0.05688  -0.0315   0.1018   1.0000
  11.000   1.1592   0.06697   0.06159  -0.0281   0.1011   1.0000
  11.250   1.1375   0.07144   0.06641  -0.0250   0.1009   1.0000
  11.500   1.1134   0.07633   0.07157  -0.0226   0.1011   1.0000
  11.750   1.0892   0.08185   0.07732  -0.0215   0.1015   1.0000
  12.000   1.0685   0.08804   0.08367  -0.0217   0.1021   1.0000
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