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OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: OAF128 AIRFOIL (oaf128-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.24 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf128-il-1000000-n5.txt
Download as CSV file: xf-oaf128-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF128 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -1.3534   0.08695   0.08338   0.0175   1.0000   0.0137
 -16.750  -1.3881   0.07786   0.07414   0.0127   1.0000   0.0136
 -16.500  -1.4221   0.06900   0.06513   0.0080   1.0000   0.0136
 -16.250  -1.4538   0.06053   0.05650   0.0033   1.0000   0.0136
 -16.000  -1.4800   0.05278   0.04860  -0.0013   1.0000   0.0136
 -15.750  -1.4992   0.04576   0.04142  -0.0059   1.0000   0.0137
 -15.500  -1.5100   0.03971   0.03522  -0.0107   1.0000   0.0137
 -15.250  -1.5160   0.03464   0.03000  -0.0151   1.0000   0.0138
 -15.000  -1.5195   0.03118   0.02640  -0.0173   1.0000   0.0139
 -14.750  -1.5087   0.02944   0.02457  -0.0175   1.0000   0.0141
 -14.500  -1.4933   0.02806   0.02312  -0.0176   1.0000   0.0142
 -14.250  -1.4754   0.02686   0.02186  -0.0176   1.0000   0.0144
 -14.000  -1.4559   0.02580   0.02072  -0.0175   1.0000   0.0146
 -13.750  -1.4350   0.02482   0.01968  -0.0175   1.0000   0.0148
 -13.500  -1.4130   0.02391   0.01871  -0.0175   1.0000   0.0150
 -13.250  -1.3901   0.02308   0.01781  -0.0176   1.0000   0.0152
 -13.000  -1.3664   0.02230   0.01697  -0.0176   1.0000   0.0154
 -12.750  -1.3419   0.02158   0.01619  -0.0177   1.0000   0.0156
 -12.500  -1.3169   0.02090   0.01546  -0.0177   1.0000   0.0158
 -12.250  -1.2916   0.02021   0.01471  -0.0179   1.0000   0.0160
 -12.000  -1.2661   0.01946   0.01392  -0.0180   1.0000   0.0163
 -11.750  -1.2399   0.01882   0.01325  -0.0182   1.0000   0.0167
 -11.500  -1.2132   0.01824   0.01264  -0.0184   1.0000   0.0170
 -11.250  -1.1861   0.01770   0.01207  -0.0185   1.0000   0.0173
 -11.000  -1.1587   0.01720   0.01154  -0.0187   1.0000   0.0177
 -10.750  -1.1310   0.01673   0.01103  -0.0189   1.0000   0.0181
 -10.500  -1.1031   0.01628   0.01055  -0.0191   1.0000   0.0185
 -10.250  -1.0749   0.01587   0.01010  -0.0193   1.0000   0.0188
 -10.000  -1.0467   0.01537   0.00958  -0.0196   1.0000   0.0193
  -9.750  -1.0182   0.01493   0.00913  -0.0199   1.0000   0.0199
  -9.500  -0.9895   0.01453   0.00872  -0.0201   1.0000   0.0206
  -9.250  -0.9606   0.01417   0.00834  -0.0204   1.0000   0.0213
  -9.000  -0.9315   0.01383   0.00798  -0.0207   1.0000   0.0219
  -8.750  -0.9024   0.01345   0.00759  -0.0210   1.0000   0.0226
  -8.500  -0.8731   0.01308   0.00723  -0.0213   1.0000   0.0235
  -8.250  -0.8436   0.01276   0.00690  -0.0216   1.0000   0.0245
  -8.000  -0.8140   0.01247   0.00659  -0.0219   1.0000   0.0254
  -7.750  -0.7876   0.01234   0.00639  -0.0214   0.9261   0.0266
  -7.500  -0.7611   0.01216   0.00613  -0.0209   0.8960   0.0281
  -7.250  -0.7333   0.01198   0.00587  -0.0207   0.8710   0.0297
  -7.000  -0.7047   0.01175   0.00559  -0.0207   0.8477   0.0322
  -6.750  -0.6758   0.01155   0.00532  -0.0208   0.8239   0.0349
  -6.500  -0.6465   0.01135   0.00506  -0.0209   0.8006   0.0385
  -6.250  -0.6170   0.01113   0.00479  -0.0212   0.7777   0.0439
  -6.000  -0.5873   0.01087   0.00451  -0.0215   0.7537   0.0529
  -5.750  -0.5574   0.01061   0.00425  -0.0218   0.7301   0.0653
  -5.500  -0.5274   0.01041   0.00403  -0.0221   0.7069   0.0776
  -5.250  -0.4974   0.01025   0.00384  -0.0225   0.6827   0.0875
  -5.000  -0.4673   0.01011   0.00366  -0.0228   0.6603   0.0967
  -4.750  -0.4372   0.00997   0.00350  -0.0231   0.6407   0.1055
  -4.500  -0.4070   0.00986   0.00336  -0.0234   0.6225   0.1134
  -4.250  -0.3768   0.00975   0.00321  -0.0237   0.6046   0.1219
  -4.000  -0.3465   0.00962   0.00307  -0.0240   0.5880   0.1322
  -3.750  -0.3162   0.00947   0.00295  -0.0244   0.5739   0.1475
  -3.500  -0.2858   0.00927   0.00283  -0.0248   0.5612   0.1732
  -3.250  -0.2555   0.00915   0.00274  -0.0252   0.5485   0.1920
  -3.000  -0.2252   0.00909   0.00265  -0.0254   0.5335   0.2012
  -2.750  -0.1949   0.00904   0.00257  -0.0257   0.5165   0.2092
  -2.500  -0.1646   0.00900   0.00249  -0.0260   0.5018   0.2175
  -2.250  -0.1343   0.00893   0.00243  -0.0263   0.4908   0.2286
  -2.000  -0.1039   0.00887   0.00237  -0.0266   0.4775   0.2440
  -1.750  -0.0736   0.00881   0.00232  -0.0269   0.4640   0.2611
  -1.500  -0.0432   0.00876   0.00228  -0.0272   0.4536   0.2769
  -1.250  -0.0129   0.00871   0.00226  -0.0275   0.4441   0.2897
  -1.000   0.0174   0.00869   0.00223  -0.0277   0.4357   0.3019
  -0.750   0.0477   0.00867   0.00222  -0.0280   0.4255   0.3154
  -0.500   0.0780   0.00865   0.00221  -0.0283   0.4160   0.3281
  -0.250   0.1083   0.00864   0.00221  -0.0285   0.4064   0.3414
   0.000   0.1386   0.00862   0.00222  -0.0288   0.3986   0.3557
   0.250   0.1688   0.00862   0.00223  -0.0290   0.3896   0.3704
   0.500   0.1991   0.00863   0.00225  -0.0293   0.3807   0.3826
   0.750   0.2293   0.00866   0.00227  -0.0295   0.3701   0.3924
   1.000   0.2595   0.00867   0.00229  -0.0298   0.3620   0.4033
   1.250   0.2897   0.00871   0.00233  -0.0300   0.3524   0.4138
   1.500   0.3199   0.00877   0.00236  -0.0302   0.3391   0.4234
   1.750   0.3501   0.00888   0.00242  -0.0305   0.3174   0.4336
   2.250   0.4103   0.00909   0.00255  -0.0311   0.2807   0.4575
   2.500   0.4404   0.00919   0.00262  -0.0314   0.2654   0.4693
   2.750   0.4705   0.00931   0.00271  -0.0317   0.2494   0.4813
   3.000   0.5005   0.00942   0.00281  -0.0320   0.2352   0.4954
   3.250   0.5306   0.00951   0.00291  -0.0322   0.2242   0.5135
   3.500   0.5606   0.00962   0.00303  -0.0325   0.2131   0.5342
   3.750   0.5906   0.00972   0.00315  -0.0328   0.2034   0.5525
   4.000   0.6205   0.00981   0.00327  -0.0331   0.1942   0.5714
   4.250   0.6504   0.00995   0.00342  -0.0334   0.1816   0.5949
   4.500   0.6803   0.01007   0.00357  -0.0337   0.1678   0.6252
   4.750   0.7101   0.01022   0.00376  -0.0340   0.1506   0.6644
   5.000   0.7397   0.01043   0.00398  -0.0343   0.1314   0.7057
   5.250   0.7691   0.01063   0.00422  -0.0346   0.1169   0.7448
   5.500   0.7982   0.01081   0.00446  -0.0348   0.1057   0.7844
   5.750   0.8270   0.01097   0.00468  -0.0348   0.0972   0.8219
   6.000   0.8552   0.01113   0.00490  -0.0347   0.0908   0.8570
   6.250   0.8823   0.01125   0.00510  -0.0344   0.0857   0.8947
   6.500   0.9056   0.01123   0.00519  -0.0331   0.0812   0.9884
   6.750   0.9348   0.01146   0.00541  -0.0333   0.0773   1.0000
   7.000   0.9640   0.01175   0.00566  -0.0335   0.0733   1.0000
   7.250   0.9931   0.01198   0.00589  -0.0337   0.0705   1.0000
   7.500   1.0221   0.01226   0.00614  -0.0339   0.0674   1.0000
   7.750   1.0509   0.01255   0.00642  -0.0340   0.0647   1.0000
   8.000   1.0797   0.01280   0.00667  -0.0342   0.0626   1.0000
   8.250   1.1083   0.01310   0.00696  -0.0343   0.0600   1.0000
   8.500   1.1367   0.01343   0.00727  -0.0344   0.0577   1.0000
   8.750   1.1651   0.01370   0.00755  -0.0345   0.0561   1.0000
   9.000   1.1934   0.01400   0.00786  -0.0346   0.0540   1.0000
   9.250   1.2213   0.01435   0.00820  -0.0347   0.0521   1.0000
   9.500   1.2491   0.01469   0.00855  -0.0347   0.0505   1.0000
   9.750   1.2769   0.01501   0.00888  -0.0348   0.0489   1.0000
  10.000   1.3043   0.01536   0.00924  -0.0348   0.0473   1.0000
  10.250   1.3314   0.01577   0.00965  -0.0348   0.0457   1.0000
  10.500   1.3585   0.01614   0.01004  -0.0348   0.0444   1.0000
  10.750   1.3854   0.01651   0.01043  -0.0347   0.0430   1.0000
  11.000   1.4119   0.01693   0.01086  -0.0347   0.0416   1.0000
  11.250   1.4379   0.01740   0.01134  -0.0345   0.0402   1.0000
  11.500   1.4639   0.01783   0.01179  -0.0344   0.0391   1.0000
  11.750   1.4896   0.01827   0.01226  -0.0343   0.0379   1.0000
  12.000   1.5148   0.01875   0.01276  -0.0341   0.0367   1.0000
  12.250   1.5393   0.01931   0.01333  -0.0338   0.0354   1.0000
  12.500   1.5636   0.01983   0.01388  -0.0335   0.0345   1.0000
  12.750   1.5877   0.02035   0.01445  -0.0332   0.0335   1.0000
  13.000   1.6110   0.02093   0.01505  -0.0328   0.0324   1.0000
  13.250   1.6332   0.02158   0.01572  -0.0324   0.0313   1.0000
  13.500   1.6549   0.02226   0.01644  -0.0319   0.0304   1.0000
  13.750   1.6762   0.02290   0.01713  -0.0313   0.0296   1.0000
  14.000   1.6964   0.02362   0.01788  -0.0306   0.0286   1.0000
  14.250   1.7149   0.02443   0.01873  -0.0298   0.0277   1.0000
  14.500   1.7311   0.02535   0.01969  -0.0288   0.0269   1.0000
  14.750   1.7463   0.02625   0.02065  -0.0277   0.0263   1.0000
  15.000   1.7590   0.02725   0.02172  -0.0264   0.0257   1.0000
  15.250   1.7653   0.02850   0.02304  -0.0245   0.0251   1.0000
  15.500   1.7671   0.03029   0.02492  -0.0232   0.0246   1.0000
  15.750   1.7696   0.03250   0.02720  -0.0228   0.0240   1.0000
  16.000   1.7711   0.03518   0.02997  -0.0231   0.0235   1.0000
  16.250   1.7719   0.03817   0.03305  -0.0238   0.0231   1.0000
  16.500   1.7723   0.04140   0.03640  -0.0249   0.0227   1.0000
  16.750   1.7697   0.04511   0.04022  -0.0262   0.0224   1.0000
  17.000   1.7638   0.04933   0.04454  -0.0278   0.0220   1.0000
  17.250   1.7543   0.05404   0.04937  -0.0295   0.0217   1.0000
  17.500   1.7413   0.05925   0.05470  -0.0315   0.0214   1.0000
  17.750   1.7248   0.06494   0.06050  -0.0336   0.0212   1.0000
  18.000   1.7050   0.07115   0.06684  -0.0360   0.0210   1.0000
  18.250   1.6826   0.07777   0.07359  -0.0385   0.0209   1.0000
  18.500   1.6600   0.08468   0.08062  -0.0414   0.0207   1.0000
  18.750   1.6360   0.09200   0.08807  -0.0445   0.0205   1.0000
  19.000   1.6120   0.09951   0.09570  -0.0479   0.0204   1.0000
  19.250   1.5882   0.10713   0.10344  -0.0514   0.0202   1.0000
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