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AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il)
Reynolds number: 100,000
Max Cl/Cd: 49.63 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12a-il-100000-n5.txt
Download as CSV file: xf-rg12a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL PROFILE12A 9.00%                        
  
 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   0.11314   0.10783  -0.0198   1.0000   0.0284
 -10.250  -0.4784   0.10923   0.10396  -0.0205   1.0000   0.0267
 -10.000  -0.4781   0.10500   0.09977  -0.0219   1.0000   0.0253
  -9.500  -0.4883   0.09268   0.08758  -0.0292   1.0000   0.0212
  -9.250  -0.4893   0.08890   0.08385  -0.0300   1.0000   0.0208
  -9.000  -0.4926   0.08457   0.07959  -0.0317   1.0000   0.0206
  -8.750  -0.4967   0.08033   0.07541  -0.0335   1.0000   0.0203
  -8.500  -0.5047   0.07553   0.07067  -0.0362   1.0000   0.0201
  -8.250  -0.5162   0.07114   0.06634  -0.0383   1.0000   0.0198
  -8.000  -0.5252   0.06658   0.06176  -0.0398   1.0000   0.0196
  -7.750  -0.5329   0.06193   0.05704  -0.0405   1.0000   0.0193
  -7.500  -0.5380   0.05742   0.05241  -0.0407   1.0000   0.0191
  -7.250  -0.5406   0.05291   0.04773  -0.0403   1.0000   0.0188
  -7.000  -0.5400   0.04852   0.04308  -0.0395   1.0000   0.0185
  -6.750  -0.5360   0.04429   0.03854  -0.0384   1.0000   0.0183
  -6.500  -0.5290   0.04015   0.03399  -0.0372   1.0000   0.0183
  -6.250  -0.5182   0.03644   0.02984  -0.0358   1.0000   0.0184
  -6.000  -0.5038   0.03331   0.02622  -0.0345   1.0000   0.0193
  -5.750  -0.4866   0.03059   0.02293  -0.0331   1.0000   0.0204
  -5.500  -0.4672   0.02843   0.02023  -0.0318   1.0000   0.0213
  -5.250  -0.4478   0.02577   0.01727  -0.0306   1.0000   0.0219
  -5.000  -0.4270   0.02390   0.01519  -0.0296   1.0000   0.0228
  -4.750  -0.4056   0.02242   0.01354  -0.0285   1.0000   0.0241
  -4.500  -0.3838   0.02111   0.01206  -0.0273   1.0000   0.0257
  -4.250  -0.3618   0.02009   0.01088  -0.0262   1.0000   0.0288
  -4.000  -0.3404   0.01908   0.00981  -0.0253   1.0000   0.0335
  -3.750  -0.3183   0.01820   0.00882  -0.0243   1.0000   0.0390
  -3.500  -0.2960   0.01740   0.00800  -0.0235   1.0000   0.0515
  -3.250  -0.2736   0.01655   0.00725  -0.0228   1.0000   0.0757
  -3.000  -0.2379   0.01565   0.00678  -0.0251   0.9947   0.1535
  -2.750  -0.2042   0.01467   0.00639  -0.0271   0.9886   0.2920
  -2.500  -0.1717   0.01362   0.00622  -0.0286   0.9829   0.5018
  -2.250  -0.1480   0.01321   0.00657  -0.0266   0.9741   0.7211
  -2.000  -0.1192   0.01325   0.00661  -0.0260   0.9650   0.7949
  -1.750  -0.0880   0.01328   0.00656  -0.0258   0.9568   0.8401
  -1.500  -0.0595   0.01325   0.00645  -0.0252   0.9467   0.8744
  -1.250  -0.0277   0.01321   0.00634  -0.0252   0.9375   0.9043
  -1.000   0.0143   0.01318   0.00618  -0.0274   0.9311   0.9312
  -0.750   0.0608   0.01315   0.00604  -0.0307   0.9235   0.9546
  -0.500   0.1170   0.01309   0.00587  -0.0362   0.9184   0.9724
  -0.250   0.1697   0.01299   0.00567  -0.0412   0.9102   0.9841
   0.000   0.2197   0.01283   0.00544  -0.0458   0.9009   0.9906
   0.250   0.2643   0.01267   0.00523  -0.0492   0.8883   0.9967
   0.500   0.3020   0.01253   0.00504  -0.0513   0.8723   1.0000
   0.750   0.3334   0.01240   0.00487  -0.0520   0.8535   1.0000
   1.000   0.3659   0.01228   0.00471  -0.0529   0.8344   1.0000
   1.250   0.3952   0.01221   0.00461  -0.0531   0.8135   1.0000
   1.500   0.4235   0.01217   0.00452  -0.0531   0.7913   1.0000
   1.750   0.4491   0.01218   0.00448  -0.0525   0.7676   1.0000
   2.000   0.4746   0.01223   0.00446  -0.0519   0.7440   1.0000
   2.250   0.4992   0.01231   0.00450  -0.0512   0.7199   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   0.6701   1.0000
   3.000   0.5702   0.01278   0.00478  -0.0484   0.6448   1.0000
   3.250   0.5939   0.01299   0.00496  -0.0475   0.6187   1.0000
   3.500   0.6175   0.01323   0.00514  -0.0465   0.5918   1.0000
   3.750   0.6410   0.01349   0.00535  -0.0456   0.5640   1.0000
   4.000   0.6644   0.01377   0.00558  -0.0447   0.5353   1.0000
   4.250   0.6875   0.01408   0.00587  -0.0438   0.5053   1.0000
   4.500   0.7104   0.01442   0.00616  -0.0428   0.4735   1.0000
   4.750   0.7331   0.01479   0.00648  -0.0418   0.4408   1.0000
   5.000   0.7553   0.01522   0.00683  -0.0408   0.4075   1.0000
   5.500   0.7990   0.01619   0.00770  -0.0388   0.3360   1.0000
   5.750   0.8203   0.01675   0.00820  -0.0378   0.2980   1.0000
   6.000   0.8412   0.01738   0.00875  -0.0367   0.2602   1.0000
   6.250   0.8616   0.01809   0.00937  -0.0357   0.2220   1.0000
   6.500   0.8809   0.01895   0.01005  -0.0346   0.1768   1.0000
   6.750   0.8987   0.02002   0.01086  -0.0335   0.1276   1.0000
   7.000   0.9173   0.02106   0.01176  -0.0324   0.0934   1.0000
   7.250   0.9353   0.02221   0.01286  -0.0311   0.0696   1.0000
   7.500   0.9514   0.02356   0.01413  -0.0296   0.0531   1.0000
   7.750   0.9682   0.02481   0.01543  -0.0281   0.0429   1.0000
   8.000   0.9835   0.02618   0.01692  -0.0264   0.0383   1.0000
   8.250   0.9991   0.02754   0.01848  -0.0248   0.0350   1.0000
   8.500   1.0136   0.02900   0.02006  -0.0231   0.0327   1.0000
   8.750   1.0261   0.03089   0.02202  -0.0213   0.0309   1.0000
   9.000   1.0425   0.03263   0.02395  -0.0199   0.0295   1.0000
   9.250   1.0588   0.03428   0.02586  -0.0185   0.0274   1.0000
   9.500   1.0733   0.03603   0.02782  -0.0171   0.0254   1.0000
   9.750   1.0867   0.03812   0.03012  -0.0157   0.0244   1.0000
  10.000   1.0982   0.04039   0.03259  -0.0142   0.0235   1.0000
  10.250   1.1071   0.04299   0.03540  -0.0126   0.0228   1.0000
  10.500   1.1111   0.04627   0.03892  -0.0107   0.0221   1.0000
  10.750   1.1089   0.04913   0.04216  -0.0081   0.0216   1.0000
  11.000   1.1025   0.05178   0.04518  -0.0056   0.0210   1.0000
  11.250   1.0928   0.05489   0.04863  -0.0035   0.0206   1.0000
  11.500   1.0802   0.05836   0.05241  -0.0023   0.0200   1.0000
  11.750   1.0659   0.06242   0.05673  -0.0022   0.0199   1.0000
  12.000   1.0488   0.06716   0.06174  -0.0032   0.0197   1.0000
  12.250   1.0306   0.07267   0.06747  -0.0054   0.0198   1.0000
  12.500   1.0100   0.07920   0.07422  -0.0091   0.0199   1.0000
  12.750   0.9890   0.08668   0.08187  -0.0139   0.0202   1.0000
  13.000   0.9670   0.09525   0.09054  -0.0197   0.0205   1.0000
  13.250   0.9463   0.10441   0.09979  -0.0258   0.0211   1.0000
  13.500   0.9257   0.11438   0.10982  -0.0322   0.0215   1.0000
  13.750   0.9083   0.12413   0.11959  -0.0379   0.0219   1.0000
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