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MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il)
Reynolds number: 50,000
Max Cl/Cd: 9.4 at α=0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-marske1-il-50000.txt
Download as CSV file: xf-marske1-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MARSKE XM-1D AIRFOIL (F14-3.0)                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4673   0.12595   0.11999   0.0261   1.0000   0.2703
 -10.000  -0.4324   0.12056   0.11464   0.0266   1.0000   0.2813
  -9.750  -0.4461   0.11851   0.11273   0.0242   1.0000   0.2906
  -9.500  -0.4165   0.11386   0.10813   0.0240   1.0000   0.3023
  -9.250  -0.4160   0.11062   0.10502   0.0222   1.0000   0.3125
  -9.000  -0.4242   0.10913   0.10365   0.0205   1.0000   0.3277
  -8.750  -0.3851   0.10332   0.09790   0.0197   1.0000   0.3376
  -8.500  -0.3845   0.10040   0.09511   0.0179   1.0000   0.3522
  -8.250  -0.3888   0.09821   0.09307   0.0161   1.0000   0.3696
  -8.000  -0.3870   0.09591   0.09092   0.0147   1.0000   0.3884
  -7.750  -0.3643   0.09207   0.08717   0.0132   1.0000   0.4085
  -7.500  -0.3182   0.08714   0.08224   0.0108   0.9357   0.4313
  -7.250  -0.2773   0.08319   0.07809   0.0073   0.8923   0.4575
  -7.000  -0.2671   0.08114   0.07594   0.0079   0.8679   0.4879
  -6.750  -0.2411   0.07846   0.07312   0.0084   0.8459   0.5109
  -6.250  -0.4280   0.05610   0.04933  -0.0257   0.8500   0.1936
  -6.000  -0.4073   0.05263   0.04590  -0.0253   0.8346   0.1869
  -5.750  -0.3996   0.04925   0.04189  -0.0240   0.8227   0.1730
  -5.500  -0.3897   0.04609   0.03797  -0.0225   0.8103   0.1616
  -5.250  -0.3701   0.04405   0.03568  -0.0215   0.7976   0.1580
  -5.000  -0.3515   0.04215   0.03347  -0.0200   0.7860   0.1548
  -4.750  -0.3303   0.04032   0.03128  -0.0192   0.7734   0.1517
  -4.500  -0.3084   0.03889   0.02949  -0.0182   0.7623   0.1506
  -4.250  -0.2845   0.03774   0.02806  -0.0173   0.7513   0.1513
  -4.000  -0.2583   0.03674   0.02683  -0.0171   0.7400   0.1523
  -3.750  -0.2323   0.03587   0.02569  -0.0160   0.7303   0.1531
  -3.500  -0.2016   0.03511   0.02478  -0.0167   0.7190   0.1541
  -3.250  -0.1698   0.03452   0.02401  -0.0165   0.7100   0.1563
  -3.000  -0.1341   0.03415   0.02351  -0.0179   0.6989   0.1605
  -2.750  -0.0991   0.03378   0.02327  -0.0187   0.6897   0.1682
  -2.500  -0.0671   0.03373   0.02317  -0.0196   0.6801   0.1770
  -2.250  -0.0421   0.03362   0.02317  -0.0187   0.6727   0.1878
  -2.000  -0.0194   0.03373   0.02345  -0.0189   0.6637   0.2040
  -1.750   0.2298   0.03287   0.02483  -0.0452   0.6414   1.0000
  -1.500   0.2504   0.03363   0.02542  -0.0452   0.6342   1.0000
  -1.250   0.2720   0.03445   0.02611  -0.0458   0.6262   1.0000
  -1.000   0.2893   0.03514   0.02661  -0.0443   0.6205   1.0000
  -0.750   0.3118   0.03639   0.02782  -0.0462   0.6132   1.0000
  -0.500   0.3303   0.03734   0.02866  -0.0460   0.6066   1.0000
  -0.250   0.3469   0.03828   0.02946  -0.0449   0.6010   1.0000
   0.000   0.3649   0.03995   0.03113  -0.0468   0.5946   1.0000
   0.250   0.3804   0.04121   0.03232  -0.0465   0.5893   1.0000
   0.500   0.3956   0.04208   0.03304  -0.0442   0.5845   1.0000
   0.750   0.4045   0.04443   0.03544  -0.0463   0.5792   1.0000
   1.000   0.4112   0.04646   0.03746  -0.0465   0.5757   1.0000
   1.250   0.4160   0.04843   0.03939  -0.0460   0.5730   1.0000
   1.500   0.4221   0.05017   0.04107  -0.0448   0.5701   1.0000
   1.750   0.4355   0.05150   0.04230  -0.0428   0.5659   1.0000
   2.000   0.4193   0.05448   0.04530  -0.0422   0.5684   1.0000
   3.000   0.2194   0.06588   0.05665  -0.0289   0.7301   1.0000
   3.250   0.2221   0.06659   0.05725  -0.0261   0.7134   1.0000
   3.500   0.2247   0.06759   0.05814  -0.0237   0.6987   1.0000
   3.750   0.2372   0.06944   0.05989  -0.0226   0.6872   1.0000
   4.250   0.2617   0.07271   0.06299  -0.0204   0.6615   1.0000
   4.500   0.2904   0.07605   0.06624  -0.0214   0.6550   1.0000
   4.750   0.2859   0.07641   0.06654  -0.0186   0.6419   1.0000
   5.000   0.2952   0.07841   0.06847  -0.0177   0.6338   1.0000
   5.250   0.3132   0.08050   0.07050  -0.0173   0.6224   1.0000
   5.500   0.3123   0.08176   0.07170  -0.0155   0.6132   1.0000
   5.750   0.3352   0.08448   0.07438  -0.0157   0.6044   1.0000
   6.000   0.3322   0.08565   0.07550  -0.0140   0.5955   1.0000
   6.250   0.3583   0.08869   0.07852  -0.0145   0.5862   1.0000
   6.500   0.3519   0.08962   0.07940  -0.0127   0.5770   1.0000
   6.750   0.3771   0.09275   0.08251  -0.0131   0.5684   1.0000
   7.000   0.3717   0.09383   0.08356  -0.0116   0.5593   1.0000
   7.250   0.3991   0.09726   0.08699  -0.0122   0.5498   1.0000
   7.500   0.3912   0.09816   0.08786  -0.0107   0.5405   1.0000
   7.750   0.4205   0.10194   0.09164  -0.0114   0.5312   1.0000
   8.000   0.4106   0.10263   0.09231  -0.0100   0.5210   1.0000
   8.250   0.4435   0.10706   0.09676  -0.0109   0.5125   1.0000
   8.500   0.4298   0.10732   0.09701  -0.0095   0.5015   1.0000
   9.000   0.4487   0.11223   0.10193  -0.0092   0.4825   1.0000
   9.250   0.4827   0.11763   0.10736  -0.0101   0.4754   1.0000
   9.500   0.4685   0.11739   0.10711  -0.0090   0.4630   1.0000
   9.750   0.4969   0.12259   0.11235  -0.0098   0.4574   1.0000
  10.000   0.4835   0.12252   0.11228  -0.0090   0.4458   1.0000
  10.250   0.5133   0.12793   0.11772  -0.0098   0.4394   1.0000
  10.500   0.4989   0.12779   0.11758  -0.0092   0.4283   1.0000
  10.750   0.5358   0.13399   0.12384  -0.0100   0.4222   1.0000
  11.000   0.5121   0.13322   0.12304  -0.0097   0.4134   1.0000
  11.250   0.5395   0.13778   0.12766  -0.0101   0.4052   1.0000
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