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WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il)
Reynolds number: 200,000
Max Cl/Cd: 78.36 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx72150a-il-200000-n5.txt
Download as CSV file: xf-fx72150a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 72-MS-150A AIRFOIL                  
  
 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   0.1634   0.10241   0.09725  -0.1332   0.7332   0.0259
 -10.250   0.1686   0.10009   0.09490  -0.1346   0.7287   0.0260
 -10.000   0.1712   0.09783   0.09264  -0.1362   0.7237   0.0261
  -9.750   0.1816   0.09514   0.08993  -0.1368   0.7188   0.0262
  -9.500   0.1943   0.09263   0.08737  -0.1369   0.7145   0.0266
  -9.250   0.2038   0.09037   0.08510  -0.1376   0.7099   0.0270
  -9.000   0.2123   0.08815   0.08287  -0.1384   0.7050   0.0274
  -8.750   0.2199   0.08590   0.08060  -0.1392   0.7005   0.0280
  -8.250   0.2293   0.08129   0.07599  -0.1419   0.6922   0.0299
  -8.000   0.2285   0.07869   0.07342  -0.1441   0.6878   0.0302
  -7.750   0.2393   0.07644   0.07114  -0.1442   0.6838   0.0303
  -7.500   0.2537   0.07461   0.06926  -0.1436   0.6803   0.0313
  -7.250   0.2612   0.07252   0.06718  -0.1443   0.6764   0.0319
  -7.000   0.2672   0.07034   0.06502  -0.1450   0.6723   0.0326
  -6.750   0.2720   0.06815   0.06283  -0.1457   0.6686   0.0332
  -6.500   0.2711   0.06578   0.06046  -0.1468   0.6651   0.0341
  -6.250   0.2703   0.06298   0.05768  -0.1498   0.6617   0.0345
  -6.000   0.2775   0.05953   0.05427  -0.1544   0.6577   0.0346
  -5.750   0.2889   0.05761   0.05235  -0.1541   0.6539   0.0349
  -5.500   0.3014   0.05563   0.05035  -0.1548   0.6504   0.0353
  -5.250   0.3159   0.05304   0.04773  -0.1577   0.6473   0.0358
  -4.750   0.3714   0.03750   0.03173  -0.1830   0.6412   0.0222
  -4.250   0.4437   0.02760   0.02082  -0.1970   0.6351   0.0191
  -4.000   0.4768   0.02536   0.01822  -0.2000   0.6324   0.0189
  -3.750   0.5108   0.02334   0.01576  -0.2027   0.6300   0.0188
  -3.500   0.5438   0.02166   0.01368  -0.2047   0.6273   0.0188
  -3.250   0.5754   0.02036   0.01205  -0.2060   0.6244   0.0190
  -3.000   0.6059   0.01937   0.01080  -0.2069   0.6216   0.0193
  -2.750   0.6350   0.01880   0.01015  -0.2077   0.6190   0.0200
  -2.500   0.6644   0.01834   0.00956  -0.2083   0.6166   0.0214
  -2.250   0.6943   0.01783   0.00884  -0.2089   0.6144   0.0227
  -2.000   0.7242   0.01737   0.00831  -0.2096   0.6125   0.0233
  -1.750   0.7530   0.01701   0.00795  -0.2101   0.6100   0.0240
  -1.500   0.7822   0.01672   0.00764  -0.2107   0.6075   0.0249
  -1.250   0.8118   0.01649   0.00735  -0.2114   0.6050   0.0263
  -1.000   0.8417   0.01629   0.00710  -0.2122   0.6026   0.0284
  -0.750   0.8717   0.01613   0.00686  -0.2129   0.6003   0.0325
  -0.500   0.9020   0.01597   0.00671  -0.2137   0.5983   0.0479
  -0.250   0.9362   0.01532   0.00665  -0.2160   0.5966   0.2738
   0.000   0.9647   0.01524   0.00708  -0.2165   0.5947   0.4956
   0.250   0.9907   0.01549   0.00739  -0.2162   0.5926   0.5453
   0.500   1.0166   0.01575   0.00766  -0.2159   0.5903   0.5785
   0.750   1.0429   0.01593   0.00782  -0.2157   0.5880   0.5934
   1.000   1.0697   0.01606   0.00791  -0.2157   0.5856   0.6005
   1.250   1.0970   0.01619   0.00797  -0.2158   0.5835   0.6061
   1.500   1.1250   0.01634   0.00803  -0.2161   0.5817   0.6127
   1.750   1.1530   0.01648   0.00812  -0.2163   0.5801   0.6175
   2.000   1.1804   0.01666   0.00827  -0.2165   0.5785   0.6222
   2.250   1.2060   0.01687   0.00850  -0.2165   0.5767   0.6272
   2.500   1.2318   0.01709   0.00874  -0.2164   0.5748   0.6319
   2.750   1.2575   0.01730   0.00898  -0.2163   0.5730   0.6367
   3.000   1.2835   0.01752   0.00922  -0.2163   0.5712   0.6428
   3.250   1.3097   0.01773   0.00944  -0.2164   0.5696   0.6491
   3.500   1.3360   0.01793   0.00966  -0.2164   0.5680   0.6547
   3.750   1.3627   0.01813   0.00988  -0.2165   0.5664   0.6614
   4.000   1.3900   0.01832   0.01007  -0.2168   0.5649   0.6680
   4.250   1.4179   0.01852   0.01027  -0.2171   0.5635   0.6756
   4.500   1.4429   0.01880   0.01063  -0.2170   0.5620   0.6842
   4.750   1.4654   0.01914   0.01106  -0.2164   0.5602   0.6936
   5.000   1.4882   0.01947   0.01149  -0.2159   0.5585   0.7043
   5.250   1.5112   0.01979   0.01190  -0.2155   0.5568   0.7169
   5.500   1.5344   0.02010   0.01232  -0.2151   0.5551   0.7313
   6.000   1.5811   0.02061   0.01306  -0.2143   0.5520   0.7787
   6.250   1.6015   0.02063   0.01329  -0.2131   0.5504   1.0000
   6.500   1.6283   0.02090   0.01358  -0.2133   0.5488   1.0000
   6.750   1.6566   0.02114   0.01382  -0.2138   0.5472   1.0000
   7.000   1.6750   0.02166   0.01444  -0.2127   0.5450   1.0000
   7.250   1.6894   0.02226   0.01519  -0.2109   0.5424   1.0000
   7.500   1.7059   0.02281   0.01584  -0.2095   0.5399   1.0000
   7.750   1.7244   0.02319   0.01629  -0.2083   0.5369   1.0000
   8.000   1.7499   0.02319   0.01630  -0.2081   0.5330   1.0000
   8.250   1.7678   0.02336   0.01651  -0.2067   0.5281   1.0000
   8.500   1.7614   0.02415   0.01743  -0.2014   0.5224   1.0000
   8.750   1.7757   0.02432   0.01763  -0.1994   0.5168   1.0000
   9.000   1.7851   0.02478   0.01816  -0.1968   0.5115   1.0000
   9.250   1.7781   0.02604   0.01957  -0.1922   0.5058   1.0000
   9.500   1.7906   0.02648   0.02005  -0.1903   0.5002   1.0000
   9.750   1.7867   0.02788   0.02157  -0.1866   0.4936   1.0000
  10.000   1.7871   0.02909   0.02286  -0.1836   0.4857   1.0000
  10.250   1.7860   0.03065   0.02452  -0.1807   0.4783   1.0000
  10.500   1.7834   0.03247   0.02643  -0.1778   0.4704   1.0000
  10.750   1.7775   0.03471   0.02879  -0.1749   0.4622   1.0000
  11.000   1.7717   0.03705   0.03122  -0.1722   0.4519   1.0000
  11.250   1.7451   0.04165   0.03599  -0.1685   0.4407   1.0000
  11.500   1.7370   0.04465   0.03904  -0.1662   0.4254   1.0000
  11.750   1.7415   0.04635   0.04066  -0.1645   0.4047   1.0000
  12.000   1.7327   0.04947   0.04365  -0.1623   0.3698   1.0000
  12.250   1.7172   0.05332   0.04720  -0.1597   0.3366   1.0000
  12.500   1.6963   0.05822   0.05192  -0.1573   0.3039   1.0000
  12.750   1.6733   0.06363   0.05715  -0.1552   0.2750   1.0000
  13.000   1.6493   0.06945   0.06278  -0.1535   0.2422   1.0000
  13.250   1.6264   0.07539   0.06853  -0.1521   0.2114   1.0000
  13.500   1.6059   0.08124   0.07419  -0.1511   0.1792   1.0000
  13.750   1.5876   0.08693   0.07969  -0.1503   0.1459   1.0000
  14.000   1.5711   0.09253   0.08508  -0.1498   0.1136   1.0000
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