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RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il)
Reynolds number: 100,000
Max Cl/Cd: 49.63 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12a189-il-100000-n5.txt
Download as CSV file: xf-rg12a189-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 12A-1.8/9.0 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4810   0.11310   0.10780  -0.0198   1.0000   0.0283
 -10.250  -0.4785   0.10918   0.10391  -0.0205   1.0000   0.0267
 -10.000  -0.4782   0.10498   0.09975  -0.0219   1.0000   0.0253
  -9.500  -0.4886   0.09256   0.08746  -0.0293   1.0000   0.0212
  -9.250  -0.4899   0.08869   0.08364  -0.0302   1.0000   0.0209
  -9.000  -0.4924   0.08464   0.07965  -0.0316   1.0000   0.0206
  -8.750  -0.4977   0.08005   0.07513  -0.0337   1.0000   0.0204
  -8.500  -0.5041   0.07567   0.07082  -0.0361   1.0000   0.0201
  -8.250  -0.5164   0.07108   0.06628  -0.0384   1.0000   0.0198
  -8.000  -0.5259   0.06641   0.06159  -0.0398   1.0000   0.0196
  -7.750  -0.5334   0.06182   0.05693  -0.0406   1.0000   0.0193
  -7.500  -0.5382   0.05739   0.05239  -0.0407   1.0000   0.0190
  -7.250  -0.5407   0.05290   0.04771  -0.0403   1.0000   0.0188
  -7.000  -0.5402   0.04848   0.04304  -0.0395   1.0000   0.0186
  -6.750  -0.5362   0.04426   0.03850  -0.0384   1.0000   0.0184
  -6.500  -0.5291   0.04014   0.03399  -0.0371   1.0000   0.0183
  -6.250  -0.5183   0.03643   0.02983  -0.0358   1.0000   0.0184
  -6.000  -0.5040   0.03331   0.02623  -0.0345   1.0000   0.0191
  -5.750  -0.4867   0.03060   0.02293  -0.0331   1.0000   0.0205
  -5.500  -0.4674   0.02838   0.02020  -0.0317   1.0000   0.0213
  -5.250  -0.4479   0.02579   0.01728  -0.0306   1.0000   0.0219
  -5.000  -0.4272   0.02392   0.01520  -0.0295   1.0000   0.0228
  -4.750  -0.4058   0.02243   0.01354  -0.0284   1.0000   0.0240
  -4.500  -0.3840   0.02112   0.01208  -0.0273   1.0000   0.0257
  -4.250  -0.3620   0.02009   0.01089  -0.0262   1.0000   0.0289
  -4.000  -0.3406   0.01907   0.00981  -0.0253   1.0000   0.0338
  -3.750  -0.3185   0.01820   0.00883  -0.0243   1.0000   0.0390
  -3.500  -0.2962   0.01741   0.00801  -0.0235   1.0000   0.0514
  -3.250  -0.2737   0.01655   0.00725  -0.0228   1.0000   0.0758
  -3.000  -0.2379   0.01565   0.00678  -0.0251   0.9947   0.1540
  -2.750  -0.2042   0.01466   0.00639  -0.0271   0.9885   0.2924
  -2.500  -0.1717   0.01361   0.00621  -0.0286   0.9828   0.5020
  -2.250  -0.1481   0.01321   0.00657  -0.0266   0.9741   0.7209
  -2.000  -0.1195   0.01325   0.00661  -0.0259   0.9651   0.7949
  -1.750  -0.0880   0.01328   0.00656  -0.0258   0.9570   0.8400
  -1.500  -0.0598   0.01325   0.00646  -0.0251   0.9468   0.8744
  -1.250  -0.0278   0.01322   0.00634  -0.0252   0.9376   0.9042
  -1.000   0.0141   0.01318   0.00620  -0.0273   0.9312   0.9312
  -0.750   0.0606   0.01315   0.00604  -0.0307   0.9236   0.9546
  -0.500   0.1171   0.01309   0.00587  -0.0362   0.9185   0.9724
  -0.250   0.1697   0.01299   0.00567  -0.0413   0.9103   0.9841
   0.000   0.2197   0.01283   0.00544  -0.0458   0.9011   0.9906
   0.250   0.2642   0.01267   0.00523  -0.0492   0.8884   0.9968
   0.500   0.3021   0.01253   0.00504  -0.0513   0.8725   1.0000
   0.750   0.3332   0.01240   0.00487  -0.0520   0.8536   1.0000
   1.000   0.3655   0.01228   0.00471  -0.0528   0.8345   1.0000
   1.250   0.3948   0.01221   0.00461  -0.0530   0.8134   1.0000
   1.500   0.4234   0.01217   0.00451  -0.0530   0.7912   1.0000
   1.750   0.4491   0.01218   0.00447  -0.0525   0.7676   1.0000
   2.000   0.4745   0.01223   0.00446  -0.0519   0.7438   1.0000
   2.250   0.4992   0.01231   0.00450  -0.0512   0.7197   1.0000
   2.500   0.5227   0.01244   0.00457  -0.0502   0.6950   1.0000
   2.750   0.5464   0.01260   0.00466  -0.0493   0.6700   1.0000
   3.000   0.5702   0.01278   0.00478  -0.0484   0.6446   1.0000
   3.250   0.5939   0.01299   0.00496  -0.0475   0.6186   1.0000
   3.500   0.6175   0.01323   0.00514  -0.0465   0.5916   1.0000
   3.750   0.6410   0.01349   0.00535  -0.0456   0.5639   1.0000
   4.000   0.6644   0.01377   0.00558  -0.0447   0.5351   1.0000
   4.250   0.6876   0.01408   0.00587  -0.0438   0.5052   1.0000
   4.500   0.7105   0.01442   0.00616  -0.0428   0.4736   1.0000
   4.750   0.7332   0.01480   0.00648  -0.0418   0.4409   1.0000
   5.000   0.7554   0.01522   0.00683  -0.0408   0.4075   1.0000
   5.250   0.7776   0.01567   0.00727  -0.0398   0.3721   1.0000
   5.500   0.7991   0.01619   0.00770  -0.0388   0.3359   1.0000
   5.750   0.8204   0.01675   0.00820  -0.0378   0.2978   1.0000
   6.000   0.8414   0.01738   0.00875  -0.0368   0.2602   1.0000
   6.250   0.8618   0.01809   0.00937  -0.0357   0.2220   1.0000
   6.500   0.8810   0.01896   0.01005  -0.0346   0.1763   1.0000
   6.750   0.8989   0.02002   0.01086  -0.0335   0.1274   1.0000
   7.000   0.9176   0.02106   0.01176  -0.0324   0.0935   1.0000
   7.250   0.9356   0.02221   0.01286  -0.0312   0.0700   1.0000
   7.500   0.9517   0.02357   0.01413  -0.0297   0.0530   1.0000
   7.750   0.9685   0.02482   0.01543  -0.0282   0.0429   1.0000
   8.000   0.9838   0.02619   0.01693  -0.0265   0.0383   1.0000
   8.250   0.9994   0.02755   0.01849  -0.0248   0.0350   1.0000
   8.500   1.0141   0.02901   0.02007  -0.0232   0.0327   1.0000
   8.750   1.0265   0.03092   0.02204  -0.0214   0.0309   1.0000
   9.000   1.0429   0.03265   0.02397  -0.0200   0.0295   1.0000
   9.250   1.0592   0.03428   0.02586  -0.0186   0.0272   1.0000
   9.500   1.0737   0.03605   0.02784  -0.0172   0.0254   1.0000
   9.750   1.0872   0.03814   0.03014  -0.0158   0.0244   1.0000
  10.000   1.0987   0.04041   0.03262  -0.0143   0.0235   1.0000
  10.250   1.1075   0.04302   0.03544  -0.0127   0.0228   1.0000
  10.500   1.1116   0.04630   0.03896  -0.0108   0.0221   1.0000
  10.750   1.1091   0.04908   0.04212  -0.0082   0.0216   1.0000
  11.000   1.1028   0.05184   0.04524  -0.0056   0.0210   1.0000
  11.250   1.0931   0.05493   0.04867  -0.0036   0.0205   1.0000
  11.500   1.0807   0.05843   0.05247  -0.0024   0.0201   1.0000
  11.750   1.0658   0.06250   0.05682  -0.0023   0.0198   1.0000
  12.000   1.0490   0.06723   0.06181  -0.0033   0.0197   1.0000
  12.250   1.0305   0.07275   0.06756  -0.0056   0.0198   1.0000
  12.500   1.0103   0.07924   0.07426  -0.0092   0.0199   1.0000
  12.750   0.9890   0.08678   0.08198  -0.0141   0.0202   1.0000
  13.000   0.9668   0.09540   0.09070  -0.0199   0.0206   1.0000
  13.250   0.9456   0.10474   0.10012  -0.0261   0.0211   1.0000
  13.500   0.9259   0.11443   0.10986  -0.0322   0.0216   1.0000
  13.750   0.9078   0.12444   0.11990  -0.0382   0.0219   1.0000
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