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D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: D.G.A. 1182 (dga1182-il)
Reynolds number: 500,000
Max Cl/Cd: 41.45 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dga1182-il-500000.txt
Download as CSV file: xf-dga1182-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: D.G.A. 1182                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6788   0.09049   0.08642   0.0126   0.1677   0.0118
  -8.250  -0.6820   0.08459   0.08055   0.0067   0.1676   0.0118
  -8.000  -0.6876   0.07812   0.07404  -0.0001   0.1676   0.0117
  -7.750  -0.6878   0.07246   0.06829  -0.0042   0.1676   0.0118
  -7.500  -0.6847   0.06763   0.06334  -0.0065   0.1676   0.0120
  -7.250  -0.6784   0.06310   0.05866  -0.0080   0.1677   0.0122
  -7.000  -0.6688   0.05878   0.05417  -0.0089   0.1677   0.0126
  -6.750  -0.6561   0.05463   0.04984  -0.0093   0.1678   0.0131
  -6.500  -0.6395   0.05071   0.04569  -0.0093   0.1679   0.0138
  -6.250  -0.6139   0.04818   0.04290  -0.0086   0.1680   0.0150
  -6.000  -0.5945   0.04526   0.03970  -0.0079   0.1681   0.0152
  -5.750  -0.5761   0.04207   0.03620  -0.0073   0.1682   0.0153
  -5.500  -0.5570   0.03891   0.03272  -0.0066   0.1683   0.0153
  -3.250  -0.3433   0.01624   0.00786  -0.0011   0.1688   0.0196
  -3.000  -0.3175   0.01487   0.00635  -0.0002   0.1678   0.0183
  -2.750  -0.2915   0.01407   0.00547   0.0002   0.1667   0.0193
  -2.500  -0.2651   0.01348   0.00480   0.0006   0.1662   0.0205
  -2.250  -0.2382   0.01315   0.00441   0.0007   0.1660   0.0230
  -2.000  -0.2111   0.01279   0.00393   0.0009   0.1657   0.0240
  -1.750  -0.1840   0.01230   0.00331   0.0011   0.1654   0.0270
  -1.500  -0.1565   0.01208   0.00301   0.0012   0.1650   0.0337
  -1.250  -0.1302   0.01145   0.00287   0.0013   0.1646   0.1979
  -1.000  -0.1036   0.01118   0.00291   0.0013   0.1641   0.3425
  -0.750  -0.0750   0.01159   0.00325   0.0012   0.1637   0.3627
  -0.500  -0.0466   0.01210   0.00366   0.0011   0.1625   0.3747
  -0.250  -0.0193   0.01265   0.00413   0.0011   0.1604   0.3835
   0.000   0.0076   0.01328   0.00459   0.0011   0.1588   0.3866
   0.250   0.0357   0.01309   0.00444   0.0011   0.1570   0.3886
   0.500   0.0633   0.01311   0.00447   0.0011   0.1548   0.3901
   0.750   0.0906   0.01328   0.00461   0.0010   0.1527   0.3916
   1.000   0.1174   0.01378   0.00501   0.0011   0.1501   0.3929
   1.250   0.1450   0.01386   0.00512   0.0010   0.1453   0.3946
   1.500   0.1717   0.01452   0.00567   0.0010   0.1390   0.3961
   1.750   0.1999   0.01421   0.00548   0.0009   0.1338   0.3973
   2.000   0.2274   0.01438   0.00563   0.0009   0.1293   0.3986
   2.250   0.2549   0.01447   0.00577   0.0008   0.1259   0.3993
   2.500   0.2831   0.01426   0.00565   0.0008   0.1212   0.4000
   2.750   0.3112   0.01415   0.00559   0.0007   0.1174   0.4005
   3.000   0.3394   0.01389   0.00542   0.0006   0.1126   0.4012
   3.250   0.3670   0.01377   0.00543   0.0006   0.0974   0.4020
   3.500   0.3977   0.01292   0.00458   0.0004   0.0870   0.4028
   3.750   0.4263   0.01277   0.00437   0.0003   0.0718   0.4038
   4.000   0.4534   0.01303   0.00464   0.0004   0.0569   0.4049
   4.250   0.4806   0.01323   0.00489   0.0005   0.0519   0.4060
   4.500   0.5076   0.01347   0.00517   0.0005   0.0481   0.4068
   4.750   0.5340   0.01389   0.00565   0.0007   0.0456   0.4075
   5.000   0.5598   0.01450   0.00636   0.0009   0.0443   0.4086
   5.250   0.5858   0.01496   0.00692   0.0011   0.0438   0.4096
   5.500   0.6119   0.01539   0.00746   0.0013   0.0426   0.4103
   5.750   0.6381   0.01577   0.00793   0.0014   0.0406   0.4109
   6.000   0.6644   0.01609   0.00831   0.0015   0.0379   0.4116
   6.250   0.6895   0.01677   0.00905   0.0018   0.0351   0.4123
   6.500   0.7132   0.01798   0.01043   0.0022   0.0323   0.4132
   6.750   0.7397   0.01818   0.01075   0.0022   0.0298   0.4143
   7.000   0.7654   0.01847   0.01114   0.0024   0.0266   0.4161
   7.250   0.7864   0.02055   0.01344   0.0030   0.0224   0.4174
   7.500   0.8139   0.02019   0.01314   0.0029   0.0203   0.4185
   7.750   0.8402   0.02027   0.01328   0.0030   0.0177   0.4194
   8.000   0.8641   0.02103   0.01410   0.0032   0.0157   0.4203
   8.250   0.8850   0.02310   0.01649   0.0039   0.0145   0.4211
   8.500   0.9073   0.02462   0.01832   0.0045   0.0134   0.4221
   8.750   0.9283   0.02645   0.02044   0.0051   0.0124   0.4230
   9.000   0.9511   0.02736   0.02149   0.0054   0.0115   0.4241
   9.250   0.9720   0.02858   0.02285   0.0057   0.0105   0.4252
   9.750   0.9480   0.04839   0.04440   0.0089   0.0100   0.4254
  10.000   0.9236   0.05849   0.05493   0.0087   0.0102   0.4251
  10.750   0.7658   0.10821   0.10467  -0.0236   0.0145   0.4214
  11.000   0.7623   0.11300   0.10946  -0.0252   0.0153   0.4217
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