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

FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 68-H-120 (fx68h120-il)
Reynolds number: 50,000
Max Cl/Cd: 28.34 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx68h120-il-50000.txt
Download as CSV file: xf-fx68h120-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 68-H-120                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3899   0.11462   0.10826  -0.0151   1.0000   0.2240
  -9.750  -0.3852   0.11137   0.10503  -0.0159   1.0000   0.2320
  -9.500  -0.3909   0.10815   0.10191  -0.0175   1.0000   0.2369
  -9.250  -0.3818   0.10448   0.09826  -0.0175   1.0000   0.2468
  -9.000  -0.3743   0.10076   0.09458  -0.0174   1.0000   0.2582
  -8.750  -0.3718   0.09754   0.09143  -0.0174   1.0000   0.2726
  -8.500  -0.3699   0.09429   0.08823  -0.0172   1.0000   0.2857
  -8.250  -0.3941   0.09287   0.08698  -0.0185   1.0000   0.2924
  -8.000  -0.5222   0.07409   0.06838  -0.0379   1.0000   0.1208
  -7.750  -0.5302   0.07100   0.06530  -0.0354   1.0000   0.1199
  -7.500  -0.5426   0.06772   0.06201  -0.0329   1.0000   0.1189
  -7.250  -0.5560   0.06412   0.05833  -0.0305   1.0000   0.1176
  -7.000  -0.5682   0.06027   0.05434  -0.0281   1.0000   0.1163
  -6.750  -0.5785   0.05610   0.04993  -0.0257   1.0000   0.1151
  -6.500  -0.5851   0.05191   0.04541  -0.0232   1.0000   0.1148
  -6.250  -0.5874   0.04786   0.04094  -0.0206   1.0000   0.1161
  -6.000  -0.5873   0.04384   0.03629  -0.0179   1.0000   0.1195
  -5.750  -0.5762   0.04216   0.03457  -0.0156   1.0000   0.1303
  -5.500  -0.5663   0.03965   0.03178  -0.0131   1.0000   0.1415
  -5.250  -0.5552   0.03755   0.02930  -0.0106   1.0000   0.1599
  -5.000  -0.5422   0.03571   0.02735  -0.0082   1.0000   0.1839
  -4.750  -0.5290   0.03436   0.02591  -0.0057   1.0000   0.2152
  -4.500  -0.5147   0.03311   0.02453  -0.0034   1.0000   0.2461
  -4.250  -0.4985   0.03198   0.02333  -0.0015   1.0000   0.2724
  -4.000  -0.4810   0.03078   0.02188   0.0002   1.0000   0.2948
  -3.750  -0.4617   0.02974   0.02075   0.0016   1.0000   0.3135
  -3.500  -0.4419   0.02879   0.01962   0.0028   1.0000   0.3312
  -3.250  -0.4209   0.02788   0.01852   0.0038   1.0000   0.3471
  -3.000  -0.3997   0.02710   0.01752   0.0048   1.0000   0.3641
  -2.750  -0.3772   0.02637   0.01667   0.0054   1.0000   0.3802
  -2.500  -0.3541   0.02571   0.01602   0.0060   1.0000   0.3993
  -2.250  -0.3301   0.02517   0.01539   0.0064   1.0000   0.4221
  -2.000  -0.3042   0.02464   0.01491   0.0064   1.0000   0.4501
  -1.750  -0.2797   0.02407   0.01452   0.0067   1.0000   0.4921
  -1.500  -0.1403   0.02263   0.01470  -0.0121   1.0000   1.0000
  -1.250  -0.1271   0.02283   0.01453  -0.0106   1.0000   1.0000
  -1.000  -0.1141   0.02310   0.01450  -0.0091   1.0000   1.0000
  -0.750  -0.1012   0.02344   0.01461  -0.0076   1.0000   1.0000
  -0.500  -0.0884   0.02385   0.01482  -0.0062   1.0000   1.0000
  -0.250  -0.0760   0.02434   0.01514  -0.0049   1.0000   1.0000
   0.000  -0.0336   0.02545   0.01606  -0.0095   0.9888   1.0000
   0.250   0.0430   0.02709   0.01748  -0.0201   0.9617   1.0000
   0.500   0.1149   0.02837   0.01860  -0.0291   0.9333   1.0000
   0.750   0.1855   0.02925   0.01941  -0.0372   0.9041   1.0000
   1.000   0.2505   0.02969   0.01979  -0.0435   0.8743   1.0000
   1.250   0.3120   0.02971   0.01982  -0.0487   0.8436   1.0000
   1.500   0.3738   0.02924   0.01938  -0.0530   0.8135   1.0000
   1.750   0.4235   0.02841   0.01857  -0.0545   0.7838   1.0000
   2.000   0.4653   0.02738   0.01756  -0.0543   0.7546   1.0000
   2.250   0.5013   0.02625   0.01640  -0.0529   0.7253   1.0000
   2.500   0.5340   0.02508   0.01518  -0.0508   0.6956   1.0000
   2.750   0.5648   0.02396   0.01399  -0.0485   0.6652   1.0000
   3.000   0.5897   0.02336   0.01323  -0.0458   0.6304   1.0000
   3.250   0.6159   0.02296   0.01258  -0.0435   0.5970   1.0000
   3.500   0.6406   0.02302   0.01234  -0.0414   0.5644   1.0000
   3.750   0.6632   0.02353   0.01265  -0.0397   0.5335   1.0000
   4.000   0.6864   0.02422   0.01310  -0.0382   0.5066   1.0000
   4.250   0.7088   0.02506   0.01379  -0.0369   0.4826   1.0000
   4.500   0.7311   0.02603   0.01465  -0.0358   0.4625   1.0000
   4.750   0.7526   0.02705   0.01565  -0.0347   0.4445   1.0000
   5.000   0.7744   0.02809   0.01669  -0.0336   0.4285   1.0000
   5.250   0.7957   0.02919   0.01779  -0.0326   0.4145   1.0000
   5.500   0.8169   0.03040   0.01905  -0.0317   0.4029   1.0000
   5.750   0.8402   0.03159   0.02020  -0.0309   0.3933   1.0000
   6.000   0.8577   0.03306   0.02192  -0.0298   0.3837   1.0000
   6.250   0.8757   0.03457   0.02357  -0.0286   0.3752   1.0000
   6.500   0.8968   0.03586   0.02491  -0.0277   0.3671   1.0000
   6.750   0.9088   0.03783   0.02715  -0.0263   0.3603   1.0000
   7.000   0.9245   0.03966   0.02916  -0.0251   0.3548   1.0000
   7.250   0.9443   0.04144   0.03103  -0.0243   0.3504   1.0000
   7.500   0.9426   0.04456   0.03455  -0.0223   0.3467   1.0000
   7.750   0.9434   0.04756   0.03783  -0.0205   0.3430   1.0000
   8.000   0.9541   0.04991   0.04038  -0.0192   0.3392   1.0000
   8.250   0.9596   0.05277   0.04339  -0.0178   0.3359   1.0000
   8.500   0.9237   0.05857   0.04942  -0.0151   0.3348   1.0000
   8.750   0.8712   0.06609   0.05694  -0.0131   0.3356   1.0000
  10.750   1.1505   0.05169   0.04317  -0.0012   0.2226   1.0000
  11.000   1.1285   0.05509   0.04694   0.0023   0.2199   1.0000
  11.250   1.0852   0.06198   0.05409   0.0052   0.2256   1.0000
  11.500   1.0623   0.06630   0.05853   0.0069   0.2246   1.0000
  11.750   1.0394   0.07130   0.06363   0.0074   0.2235   1.0000
  12.000   1.1395   0.05302   0.04536   0.0138   0.1760   1.0000
  12.250   1.1343   0.05382   0.04624   0.0158   0.1655   1.0000
  12.500   1.1144   0.05740   0.05007   0.0165   0.1588   1.0000
  12.750   1.0984   0.06083   0.05363   0.0166   0.1506   1.0000
  13.000   1.0721   0.06688   0.05992   0.0150   0.1468   1.0000
  13.250   1.0588   0.07122   0.06436   0.0135   0.1391   1.0000
  13.500   1.0296   0.07937   0.07268   0.0100   0.1393   1.0000
  13.750   0.9967   0.08901   0.08234   0.0056   0.1402   1.0000
<< Back to FX 68-H-120 (fx68h120-il)

Polar data table (+)

Polar graphs


<< Back to FX 68-H-120 (fx68h120-il)