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AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AH 83-150 Q (ah83150q-il)
Reynolds number: 200,000
Max Cl/Cd: 71.7 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah83150q-il-200000-n5.txt
Download as CSV file: xf-ah83150q-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 83-150 Q                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2338   0.10506   0.10048  -0.0544   0.7340   0.0246
 -10.250  -0.2404   0.09978   0.09523  -0.0595   0.7320   0.0254
 -10.000  -0.2431   0.09491   0.09041  -0.0636   0.7298   0.0255
  -9.750  -0.2246   0.09404   0.08953  -0.0599   0.7274   0.0272
  -9.500  -0.2229   0.09017   0.08568  -0.0620   0.7252   0.0271
  -9.250  -0.2216   0.08633   0.08185  -0.0643   0.7230   0.0271
  -9.000  -0.2183   0.08311   0.07863  -0.0659   0.7209   0.0285
  -8.750  -0.2191   0.07907   0.07460  -0.0687   0.7189   0.0292
  -8.500  -0.2252   0.07401   0.06954  -0.0730   0.7168   0.0297
  -8.250  -0.2326   0.06943   0.06498  -0.0766   0.7142   0.0297
  -7.250  -0.2718   0.05513   0.04973  -0.0776   0.7048   0.0318
  -6.750  -0.2591   0.04161   0.03572  -0.0754   0.7016   0.0161
  -6.500  -0.2449   0.03940   0.03342  -0.0750   0.6993   0.0158
  -6.250  -0.2303   0.03689   0.03071  -0.0743   0.6968   0.0153
  -6.000  -0.2145   0.03410   0.02761  -0.0734   0.6945   0.0147
  -5.750  -0.1969   0.03102   0.02411  -0.0722   0.6925   0.0139
  -5.250  -0.1528   0.02603   0.01806  -0.0698   0.6887   0.0127
  -5.000  -0.1285   0.02449   0.01627  -0.0694   0.6869   0.0126
  -4.750  -0.1032   0.02313   0.01463  -0.0689   0.6851   0.0126
  -4.500  -0.0771   0.02194   0.01327  -0.0686   0.6827   0.0127
  -4.250  -0.0508   0.02091   0.01209  -0.0683   0.6805   0.0127
  -4.000  -0.0249   0.01991   0.01101  -0.0681   0.6782   0.0129
  -3.750   0.0007   0.01905   0.01011  -0.0678   0.6760   0.0133
  -3.500   0.0261   0.01836   0.00938  -0.0674   0.6739   0.0137
  -3.250   0.0516   0.01776   0.00873  -0.0671   0.6721   0.0143
  -3.000   0.0772   0.01727   0.00818  -0.0668   0.6705   0.0150
  -2.750   0.1027   0.01686   0.00774  -0.0666   0.6685   0.0172
  -2.500   0.1283   0.01653   0.00741  -0.0665   0.6658   0.0190
  -2.250   0.1544   0.01621   0.00703  -0.0663   0.6632   0.0205
  -2.000   0.1807   0.01591   0.00669  -0.0662   0.6610   0.0226
  -1.750   0.2073   0.01564   0.00638  -0.0660   0.6589   0.0279
  -1.500   0.2306   0.01477   0.00606  -0.0658   0.6570   0.1599
  -1.250   0.2310   0.01320   0.00684  -0.0600   0.6552   0.7426
  -1.000   0.2491   0.01420   0.00781  -0.0564   0.6533   0.8307
  -0.750   0.2620   0.01482   0.00847  -0.0517   0.6504   0.8607
  -0.500   0.2822   0.01500   0.00860  -0.0496   0.6476   0.8745
  -0.250   0.3071   0.01498   0.00851  -0.0487   0.6450   0.8788
   0.000   0.3344   0.01495   0.00836  -0.0488   0.6427   0.8813
   0.250   0.3625   0.01490   0.00820  -0.0490   0.6406   0.8835
   0.500   0.3912   0.01487   0.00804  -0.0494   0.6387   0.8855
   0.750   0.4175   0.01494   0.00811  -0.0496   0.6351   0.8877
   1.000   0.4445   0.01496   0.00810  -0.0498   0.6318   0.8893
   1.250   0.4719   0.01494   0.00802  -0.0500   0.6289   0.8905
   1.500   0.4997   0.01490   0.00792  -0.0502   0.6264   0.8919
   1.750   0.5283   0.01486   0.00781  -0.0505   0.6242   0.8932
   2.000   0.5552   0.01491   0.00786  -0.0507   0.6210   0.8945
   2.250   0.5815   0.01498   0.00794  -0.0508   0.6170   0.8959
   2.500   0.6089   0.01498   0.00794  -0.0510   0.6136   0.8976
   2.750   0.6376   0.01495   0.00787  -0.0515   0.6108   0.8989
   3.000   0.6673   0.01490   0.00777  -0.0520   0.6084   0.8999
   3.250   0.6927   0.01504   0.00797  -0.0522   0.6035   0.9012
   3.500   0.7202   0.01508   0.00803  -0.0525   0.5993   0.9025
   3.750   0.7481   0.01502   0.00796  -0.0527   0.5958   0.9037
   4.000   0.7763   0.01496   0.00789  -0.0530   0.5927   0.9048
   4.250   0.8005   0.01509   0.00811  -0.0528   0.5870   0.9060
   4.500   0.8277   0.01509   0.00814  -0.0530   0.5826   0.9070
   4.750   0.8564   0.01502   0.00806  -0.0533   0.5791   0.9079
   5.000   0.8807   0.01515   0.00828  -0.0532   0.5731   0.9094
   5.250   0.9069   0.01517   0.00835  -0.0532   0.5679   0.9109
   5.500   0.9357   0.01510   0.00828  -0.0536   0.5637   0.9122
   5.750   0.9590   0.01528   0.00858  -0.0533   0.5563   0.9136
   6.000   0.9865   0.01526   0.00857  -0.0536   0.5505   0.9147
   6.250   1.0109   0.01538   0.00879  -0.0535   0.5427   0.9159
   6.750   1.0598   0.01536   0.00881  -0.0529   0.5211   0.9184
   7.000   1.0810   0.01543   0.00892  -0.0520   0.5075   0.9202
   7.250   1.1026   0.01557   0.00911  -0.0513   0.4956   0.9221
   7.500   1.1242   0.01575   0.00931  -0.0507   0.4839   0.9237
   7.750   1.1450   0.01597   0.00956  -0.0500   0.4714   0.9255
   8.000   1.1639   0.01625   0.00984  -0.0490   0.4570   0.9274
   8.250   1.1809   0.01660   0.01020  -0.0478   0.4420   0.9295
   8.500   1.1938   0.01701   0.01060  -0.0459   0.4269   0.9319
   8.750   1.2035   0.01754   0.01113  -0.0436   0.4109   0.9352
   9.000   1.2124   0.01822   0.01181  -0.0415   0.3947   0.9395
   9.250   1.2212   0.01905   0.01263  -0.0397   0.3784   0.9442
   9.500   1.2302   0.02003   0.01361  -0.0383   0.3616   0.9494
   9.750   1.2391   0.02120   0.01477  -0.0373   0.3437   0.9570
  10.000   1.2462   0.02259   0.01614  -0.0365   0.3232   0.9817
  10.250   1.2487   0.02423   0.01771  -0.0351   0.3012   1.0000
  10.500   1.2494   0.02609   0.01946  -0.0338   0.2795   1.0000
  10.750   1.2514   0.02794   0.02125  -0.0326   0.2577   1.0000
  11.000   1.2527   0.02989   0.02312  -0.0315   0.2380   1.0000
  11.250   1.2555   0.03178   0.02496  -0.0305   0.2208   1.0000
  11.500   1.2584   0.03370   0.02685  -0.0296   0.2038   1.0000
  11.750   1.2616   0.03565   0.02876  -0.0288   0.1886   1.0000
  12.000   1.2646   0.03765   0.03074  -0.0281   0.1743   1.0000
  12.250   1.2683   0.03967   0.03275  -0.0275   0.1624   1.0000
  12.500   1.2720   0.04175   0.03481  -0.0269   0.1513   1.0000
  12.750   1.2776   0.04373   0.03681  -0.0265   0.1408   1.0000
  13.000   1.2825   0.04580   0.03891  -0.0261   0.1321   1.0000
  13.250   1.2865   0.04803   0.04116  -0.0258   0.1240   1.0000
  13.500   1.2928   0.05006   0.04326  -0.0256   0.1160   1.0000
  13.750   1.2965   0.05242   0.04563  -0.0254   0.1087   1.0000
  14.000   1.3017   0.05468   0.04795  -0.0254   0.1007   1.0000
  14.250   1.3058   0.05708   0.05041  -0.0253   0.0935   1.0000
  14.500   1.3084   0.05970   0.05305  -0.0254   0.0861   1.0000
  14.750   1.3126   0.06221   0.05563  -0.0255   0.0793   1.0000
  15.000   1.3133   0.06518   0.05863  -0.0257   0.0735   1.0000
  15.250   1.3170   0.06783   0.06137  -0.0260   0.0678   1.0000
  15.500   1.3171   0.07099   0.06457  -0.0264   0.0635   1.0000
  15.750   1.3195   0.07390   0.06758  -0.0268   0.0597   1.0000
  16.000   1.3198   0.07716   0.07089  -0.0274   0.0552   1.0000
  16.250   1.3181   0.08074   0.07450  -0.0281   0.0522   1.0000
  16.500   1.3209   0.08374   0.07764  -0.0287   0.0488   1.0000
  16.750   1.3200   0.08731   0.08127  -0.0296   0.0457   1.0000
  17.000   1.3166   0.09132   0.08533  -0.0307   0.0435   1.0000
  17.250   1.3187   0.09457   0.08872  -0.0317   0.0414   1.0000
  17.500   1.3192   0.09810   0.09238  -0.0328   0.0391   1.0000
  17.750   1.3170   0.10210   0.09646  -0.0342   0.0369   1.0000
  18.000   1.3121   0.10656   0.10097  -0.0358   0.0351   1.0000
  18.250   1.3138   0.11004   0.10462  -0.0371   0.0330   1.0000
  18.500   1.3128   0.11399   0.10869  -0.0387   0.0311   1.0000
  18.750   1.3090   0.11847   0.11327  -0.0406   0.0294   1.0000
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