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

FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 79-L-100 (fx79l100-il)
Reynolds number: 100,000
Max Cl/Cd: 35.92 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx79l100-il-100000-n5.txt
Download as CSV file: xf-fx79l100-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-L-100                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7401   0.09085   0.08566  -0.0056   1.0000   0.0301
 -11.250  -0.7747   0.07827   0.07302  -0.0150   1.0000   0.0294
 -11.000  -0.8082   0.06900   0.06360  -0.0220   1.0000   0.0286
 -10.750  -0.8349   0.06263   0.05703  -0.0256   1.0000   0.0282
 -10.500  -0.8554   0.05826   0.05246  -0.0265   1.0000   0.0286
 -10.250  -0.8728   0.05458   0.04856  -0.0252   1.0000   0.0286
 -10.000  -0.8843   0.05076   0.04443  -0.0236   1.0000   0.0289
  -9.750  -0.8893   0.04711   0.04041  -0.0220   1.0000   0.0294
  -9.500  -0.8887   0.04360   0.03649  -0.0204   1.0000   0.0300
  -9.250  -0.8834   0.04034   0.03278  -0.0187   1.0000   0.0308
  -9.000  -0.8741   0.03755   0.02945  -0.0170   1.0000   0.0322
  -8.750  -0.8601   0.03535   0.02709  -0.0160   1.0000   0.0338
  -8.500  -0.8433   0.03378   0.02541  -0.0150   1.0000   0.0356
  -8.250  -0.8254   0.03193   0.02331  -0.0139   1.0000   0.0373
  -8.000  -0.8060   0.03006   0.02114  -0.0128   1.0000   0.0394
  -7.750  -0.7853   0.02863   0.01936  -0.0118   1.0000   0.0419
  -7.500  -0.7656   0.02700   0.01778  -0.0109   1.0000   0.0446
  -7.250  -0.7446   0.02575   0.01645  -0.0100   1.0000   0.0475
  -7.000  -0.7232   0.02452   0.01508  -0.0090   1.0000   0.0506
  -6.750  -0.7025   0.02336   0.01382  -0.0079   1.0000   0.0548
  -6.500  -0.6820   0.02237   0.01284  -0.0069   1.0000   0.0591
  -6.250  -0.6612   0.02142   0.01180  -0.0057   1.0000   0.0636
  -6.000  -0.6415   0.02048   0.01089  -0.0045   1.0000   0.0700
  -5.750  -0.6208   0.01971   0.01003  -0.0033   1.0000   0.0774
  -5.500  -0.6014   0.01884   0.00919  -0.0021   1.0000   0.0858
  -5.250  -0.5813   0.01808   0.00847  -0.0008   1.0000   0.0982
  -5.000  -0.5614   0.01731   0.00777   0.0004   1.0000   0.1147
  -4.750  -0.5420   0.01651   0.00712   0.0017   1.0000   0.1418
  -4.500  -0.5237   0.01562   0.00651   0.0031   1.0000   0.1912
  -4.250  -0.5078   0.01457   0.00595   0.0048   1.0000   0.2812
  -4.000  -0.4926   0.01371   0.00570   0.0069   1.0000   0.3955
  -3.750  -0.4744   0.01334   0.00562   0.0088   1.0000   0.4759
  -3.500  -0.4549   0.01315   0.00556   0.0105   1.0000   0.5247
  -3.250  -0.4356   0.01303   0.00549   0.0123   1.0000   0.5622
  -3.000  -0.4113   0.01293   0.00542   0.0129   0.9914   0.5942
  -2.750  -0.3742   0.01290   0.00541   0.0111   0.9739   0.6284
  -2.500  -0.3366   0.01289   0.00540   0.0094   0.9572   0.6586
  -2.250  -0.2991   0.01286   0.00538   0.0077   0.9405   0.6832
  -2.000  -0.2612   0.01281   0.00529   0.0058   0.9237   0.7026
  -1.750  -0.2234   0.01274   0.00516   0.0040   0.9072   0.7167
  -1.500  -0.1870   0.01268   0.00505   0.0025   0.8908   0.7291
  -1.250  -0.1525   0.01262   0.00495   0.0014   0.8742   0.7408
  -1.000  -0.1200   0.01258   0.00485   0.0007   0.8578   0.7525
  -0.750  -0.0894   0.01255   0.00477   0.0004   0.8422   0.7646
  -0.500  -0.0593   0.01253   0.00473   0.0002   0.8275   0.7759
  -0.250  -0.0297   0.01252   0.00470   0.0001   0.8135   0.7877
   0.000   0.0000   0.01251   0.00469   0.0000   0.8003   0.8002
   0.250   0.0296   0.01252   0.00470  -0.0001   0.7878   0.8136
   0.500   0.0592   0.01253   0.00473  -0.0002   0.7759   0.8276
   0.750   0.0893   0.01255   0.00477  -0.0004   0.7646   0.8424
   1.000   0.1199   0.01258   0.00485  -0.0007   0.7525   0.8579
   1.250   0.1524   0.01262   0.00495  -0.0014   0.7408   0.8741
   1.500   0.1869   0.01268   0.00506  -0.0025   0.7293   0.8906
   1.750   0.2235   0.01274   0.00516  -0.0041   0.7170   0.9073
   2.000   0.2611   0.01281   0.00529  -0.0059   0.7025   0.9237
   2.250   0.2990   0.01286   0.00538  -0.0077   0.6834   0.9404
   2.500   0.3365   0.01288   0.00539  -0.0094   0.6586   0.9571
   2.750   0.3739   0.01290   0.00540  -0.0111   0.6281   0.9738
   3.000   0.4112   0.01293   0.00542  -0.0129   0.5943   0.9914
   3.250   0.4356   0.01303   0.00549  -0.0123   0.5624   1.0000
   3.500   0.4549   0.01315   0.00556  -0.0106   0.5251   1.0000
   3.750   0.4743   0.01334   0.00562  -0.0088   0.4750   1.0000
   4.000   0.4925   0.01371   0.00569  -0.0069   0.3949   1.0000
   4.250   0.5077   0.01457   0.00594  -0.0048   0.2817   1.0000
   4.500   0.5236   0.01562   0.00649  -0.0031   0.1908   1.0000
   4.750   0.5420   0.01650   0.00712  -0.0018   0.1429   1.0000
   5.000   0.5613   0.01731   0.00776  -0.0005   0.1145   1.0000
   5.250   0.5812   0.01808   0.00847   0.0008   0.0982   1.0000
   5.500   0.6012   0.01884   0.00920   0.0020   0.0860   1.0000
   5.750   0.6207   0.01970   0.01003   0.0033   0.0776   1.0000
   6.000   0.6415   0.02047   0.01087   0.0045   0.0702   1.0000
   6.250   0.6610   0.02143   0.01179   0.0057   0.0641   1.0000
   6.500   0.6820   0.02236   0.01284   0.0069   0.0592   1.0000
   6.750   0.7025   0.02336   0.01383   0.0079   0.0550   1.0000
   7.000   0.7231   0.02454   0.01510   0.0090   0.0506   1.0000
   7.250   0.7446   0.02574   0.01645   0.0100   0.0474   1.0000
   7.500   0.7656   0.02701   0.01779   0.0109   0.0446   1.0000
   7.750   0.7852   0.02858   0.01933   0.0118   0.0417   1.0000
   8.000   0.8058   0.03003   0.02113   0.0128   0.0390   1.0000
   8.250   0.8252   0.03192   0.02331   0.0139   0.0371   1.0000
   8.500   0.8431   0.03358   0.02518   0.0150   0.0351   1.0000
   8.750   0.8601   0.03507   0.02673   0.0158   0.0333   1.0000
   9.000   0.8731   0.03746   0.02945   0.0172   0.0315   1.0000
   9.250   0.8831   0.04034   0.03280   0.0187   0.0305   1.0000
   9.500   0.8881   0.04365   0.03656   0.0204   0.0297   1.0000
   9.750   0.8889   0.04711   0.04042   0.0220   0.0291   1.0000
  10.000   0.8840   0.05078   0.04445   0.0236   0.0287   1.0000
  10.250   0.8731   0.05453   0.04850   0.0251   0.0284   1.0000
  10.500   0.8552   0.05828   0.05248   0.0265   0.0285   1.0000
  10.750   0.8316   0.06316   0.05758   0.0254   0.0284   1.0000
  11.000   0.8060   0.06946   0.06406   0.0216   0.0288   1.0000
  11.250   0.7743   0.07846   0.07321   0.0148   0.0293   1.0000
  11.500   0.7368   0.09211   0.08692   0.0045   0.0299   1.0000
<< Back to FX 79-L-100 (fx79l100-il)

Polar data table (+)

Polar graphs


<< Back to FX 79-L-100 (fx79l100-il)