Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 38-153 AIRFOIL (fx38153-il)
Reynolds number: 1,000,000
Max Cl/Cd: 91.47 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx38153-il-1000000.txt
Download as CSV file: xf-fx38153-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 38-153 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.1825   0.08507   0.08327  -0.1164   0.9695   0.0128
 -12.250  -0.1924   0.07868   0.07690  -0.1188   0.9685   0.0130
 -12.000  -0.2117   0.06935   0.06758  -0.1229   0.9675   0.0130
 -11.750  -0.2815   0.05076   0.04880  -0.1329   0.9659   0.0123
 -11.500  -0.3156   0.04385   0.04175  -0.1347   0.9634   0.0122
 -11.250  -0.3378   0.03939   0.03716  -0.1347   0.9608   0.0122
 -11.000  -0.3570   0.03562   0.03326  -0.1339   0.9584   0.0122
 -10.750  -0.3717   0.03267   0.03018  -0.1325   0.9558   0.0123
 -10.500  -0.3837   0.03025   0.02764  -0.1306   0.9529   0.0124
 -10.250  -0.3932   0.02807   0.02535  -0.1283   0.9497   0.0127
 -10.000  -0.4010   0.02599   0.02312  -0.1258   0.9461   0.0130
  -9.750  -0.4521   0.03690   0.03369  -0.1233   0.9444   0.0127
  -9.500  -0.4522   0.03601   0.03227  -0.1196   0.9414   0.0144
  -9.250  -0.4506   0.03471   0.03064  -0.1169   0.9386   0.0145
  -8.750  -0.4366   0.02121   0.01625  -0.1114   0.9346   0.0095
  -8.500  -0.4068   0.01827   0.01307  -0.1107   0.9344   0.0080
  -8.250  -0.3810   0.01699   0.01167  -0.1105   0.9333   0.0080
  -8.000  -0.3605   0.01624   0.01086  -0.1096   0.9317   0.0081
  -7.750  -0.3410   0.01561   0.01016  -0.1085   0.9300   0.0082
  -7.500  -0.3215   0.01504   0.00954  -0.1074   0.9283   0.0083
  -7.250  -0.3014   0.01450   0.00895  -0.1065   0.9268   0.0084
  -7.000  -0.2802   0.01402   0.00842  -0.1058   0.9251   0.0085
  -6.750  -0.2623   0.01364   0.00801  -0.1045   0.9229   0.0085
  -6.500  -0.2449   0.01330   0.00763  -0.1031   0.9204   0.0086
  -6.250  -0.2253   0.01294   0.00724  -0.1020   0.9180   0.0086
  -6.000  -0.2029   0.01258   0.00685  -0.1015   0.9160   0.0087
  -5.750  -0.1786   0.01226   0.00650  -0.1013   0.9144   0.0089
  -5.500  -0.1536   0.01191   0.00612  -0.1012   0.9131   0.0091
  -5.250  -0.1269   0.01162   0.00580  -0.1014   0.9119   0.0093
  -5.000  -0.0989   0.01136   0.00552  -0.1019   0.9108   0.0095
  -4.750  -0.0712   0.01118   0.00532  -0.1022   0.9091   0.0097
  -4.500  -0.0507   0.01099   0.00514  -0.1010   0.9057   0.0101
  -4.250  -0.0255   0.01077   0.00493  -0.1008   0.9028   0.0109
  -4.000   0.0028   0.01052   0.00469  -0.1012   0.9005   0.0137
  -3.750   0.0334   0.01026   0.00441  -0.1020   0.8985   0.0160
  -3.500   0.0654   0.01001   0.00415  -0.1031   0.8968   0.0180
  -3.250   0.0970   0.00982   0.00395  -0.1042   0.8952   0.0198
  -3.000   0.1223   0.00967   0.00382  -0.1040   0.8924   0.0227
  -2.750   0.1463   0.00944   0.00365  -0.1035   0.8883   0.0388
  -2.500   0.1766   0.00905   0.00333  -0.1043   0.8842   0.0659
  -2.250   0.2091   0.00859   0.00300  -0.1056   0.8806   0.1143
  -2.000   0.2330   0.00787   0.00272  -0.1057   0.8755   0.2500
  -1.750   0.2728   0.00590   0.00204  -0.1110   0.8702   0.6158
  -1.500   0.3090   0.00556   0.00199  -0.1130   0.8657   0.7092
  -1.250   0.3371   0.00556   0.00200  -0.1132   0.8606   0.7231
  -1.000   0.3653   0.00558   0.00204  -0.1134   0.8560   0.7325
  -0.750   0.3962   0.00557   0.00200  -0.1141   0.8516   0.7408
  -0.500   0.4227   0.00562   0.00206  -0.1139   0.8429   0.7484
  -0.250   0.4512   0.00566   0.00206  -0.1140   0.8320   0.7562
   0.000   0.4771   0.00578   0.00217  -0.1135   0.8205   0.7626
   0.250   0.5041   0.00587   0.00222  -0.1134   0.8069   0.7670
   0.500   0.5314   0.00595   0.00222  -0.1134   0.7900   0.7701
   0.750   0.5552   0.00607   0.00228  -0.1125   0.7681   0.7726
   1.000   0.5750   0.00633   0.00242  -0.1108   0.7357   0.7755
   1.250   0.5903   0.00674   0.00265  -0.1080   0.6927   0.7799
   1.500   0.6038   0.00723   0.00290  -0.1051   0.6433   0.7843
   1.750   0.6125   0.00769   0.00313  -0.1012   0.5904   0.7872
   2.000   0.6207   0.00821   0.00342  -0.0972   0.5353   0.7894
   2.250   0.6346   0.00871   0.00370  -0.0946   0.4833   0.7914
   2.500   0.6512   0.00924   0.00397  -0.0927   0.4279   0.7930
   2.750   0.6703   0.00973   0.00423  -0.0913   0.3782   0.7946
   3.000   0.6908   0.01019   0.00447  -0.0903   0.3353   0.7962
   3.250   0.7123   0.01064   0.00471  -0.0895   0.2920   0.7977
   3.500   0.7342   0.01106   0.00495  -0.0888   0.2548   0.7990
   3.750   0.7562   0.01149   0.00521  -0.0882   0.2221   0.8001
   4.000   0.7777   0.01192   0.00546  -0.0874   0.1854   0.8013
   4.250   0.8002   0.01225   0.00568  -0.0868   0.1640   0.8024
   4.500   0.8215   0.01265   0.00596  -0.0860   0.1364   0.8034
   4.750   0.8441   0.01297   0.00621  -0.0854   0.1231   0.8044
   5.000   0.8657   0.01334   0.00650  -0.0845   0.1021   0.8055
   5.250   0.8866   0.01376   0.00683  -0.0836   0.0852   0.8066
   5.500   0.9093   0.01408   0.00711  -0.0831   0.0707   0.8077
   5.750   0.9298   0.01455   0.00748  -0.0821   0.0548   0.8089
   6.000   0.9527   0.01488   0.00778  -0.0816   0.0485   0.8101
   6.250   0.9746   0.01527   0.00813  -0.0810   0.0362   0.8112
   6.500   0.9966   0.01566   0.00848  -0.0803   0.0306   0.8123
   6.750   1.0195   0.01599   0.00880  -0.0799   0.0289   0.8133
   7.000   1.0424   0.01631   0.00913  -0.0794   0.0274   0.8143
   7.250   1.0652   0.01663   0.00947  -0.0789   0.0261   0.8153
   7.500   1.0880   0.01695   0.00982  -0.0785   0.0249   0.8161
   8.000   1.1292   0.01781   0.01066  -0.0769   0.0163   0.8183
   8.250   1.1495   0.01822   0.01109  -0.0760   0.0158   0.8192
   8.500   1.1696   0.01865   0.01156  -0.0751   0.0155   0.8200
   8.750   1.1892   0.01912   0.01205  -0.0742   0.0150   0.8209
   9.000   1.2084   0.01961   0.01258  -0.0732   0.0146   0.8218
   9.250   1.2270   0.02014   0.01313  -0.0721   0.0141   0.8228
   9.500   1.2454   0.02068   0.01372  -0.0710   0.0136   0.8237
   9.750   1.2635   0.02126   0.01434  -0.0699   0.0133   0.8247
  10.000   1.2812   0.02186   0.01499  -0.0688   0.0130   0.8257
  10.250   1.2985   0.02248   0.01566  -0.0676   0.0128   0.8267
  10.500   1.3154   0.02312   0.01636  -0.0664   0.0126   0.8278
  10.750   1.3318   0.02381   0.01711  -0.0652   0.0123   0.8289
  11.000   1.3472   0.02457   0.01791  -0.0639   0.0121   0.8299
  11.250   1.3618   0.02538   0.01878  -0.0625   0.0117   0.8308
  11.500   1.3754   0.02627   0.01973  -0.0610   0.0113   0.8315
  11.750   1.3872   0.02727   0.02080  -0.0594   0.0110   0.8322
  12.000   1.3978   0.02838   0.02198  -0.0577   0.0106   0.8334
  12.250   1.4055   0.02967   0.02336  -0.0556   0.0102   0.8344
  12.500   1.4189   0.03055   0.02431  -0.0543   0.0099   0.8353
  12.750   1.4343   0.03129   0.02511  -0.0533   0.0097   0.8362
  13.000   1.4495   0.03205   0.02592  -0.0523   0.0092   0.8371
  13.250   1.4631   0.03296   0.02689  -0.0512   0.0087   0.8380
  13.500   1.4768   0.03388   0.02784  -0.0502   0.0080   0.8390
  13.750   1.4842   0.03531   0.02934  -0.0486   0.0074   0.8400
  14.000   1.5049   0.03567   0.02972  -0.0484   0.0068   0.8412
  14.250   1.5203   0.03648   0.03058  -0.0476   0.0057   0.8424
  14.500   1.5328   0.03755   0.03162  -0.0467   0.0035   0.8435
  14.750   1.5398   0.03912   0.03320  -0.0454   0.0031   0.8446
  15.000   1.5453   0.04088   0.03502  -0.0440   0.0027   0.8455
  15.250   1.5510   0.04269   0.03689  -0.0428   0.0025   0.8463
  15.500   1.5554   0.04465   0.03894  -0.0416   0.0025   0.8470
  15.750   1.5587   0.04679   0.04118  -0.0406   0.0024   0.8480
  16.000   1.5606   0.04913   0.04363  -0.0396   0.0023   0.8491
  16.250   1.5613   0.05167   0.04630  -0.0387   0.0023   0.8502
  16.500   1.5606   0.05445   0.04919  -0.0380   0.0022   0.8513
  16.750   1.5586   0.05746   0.05233  -0.0374   0.0022   0.8524
  17.000   1.5562   0.06062   0.05561  -0.0371   0.0022   0.8534
  17.250   1.5519   0.06414   0.05926  -0.0370   0.0021   0.8544
  17.500   1.5462   0.06799   0.06323  -0.0372   0.0021   0.8554
  17.750   1.5393   0.07212   0.06750  -0.0376   0.0021   0.8563
  18.000   1.5302   0.07666   0.07217  -0.0384   0.0021   0.8572
  18.250   1.5190   0.08165   0.07729  -0.0395   0.0020   0.8581
  18.500   1.5071   0.08689   0.08267  -0.0409   0.0020   0.8589
  18.750   1.4939   0.09248   0.08840  -0.0427   0.0020   0.8596
  19.000   1.4780   0.09862   0.09467  -0.0449   0.0020   0.8603
  19.250   1.4614   0.10498   0.10118  -0.0474   0.0020   0.8609
<< Back to FX 38-153 AIRFOIL (fx38153-il)

Polar data table (+)

Polar graphs


<< Back to FX 38-153 AIRFOIL (fx38153-il)