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FX 84-W-218 (fx84w218-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 84-W-218 (fx84w218-il)
Reynolds number: 50,000
Max Cl/Cd: 2.8 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx84w218-il-50000.txt
Download as CSV file: xf-fx84w218-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-218                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.7217   0.09082   0.08430  -0.0319   1.0000   0.2227
  -8.750  -0.7735   0.08558   0.07903  -0.0282   1.0000   0.2211
  -8.500  -0.8302   0.07967   0.07298  -0.0241   1.0000   0.2193
  -8.250  -0.8797   0.07373   0.06677  -0.0200   1.0000   0.2185
  -8.000  -0.9122   0.06867   0.06136  -0.0166   1.0000   0.2194
  -7.750  -0.9349   0.06411   0.05635  -0.0135   1.0000   0.2214
  -7.500  -0.9457   0.06035   0.05215  -0.0110   1.0000   0.2243
  -7.250  -0.9284   0.05979   0.05182  -0.0098   1.0000   0.2296
  -7.000  -0.9251   0.05770   0.04953  -0.0080   1.0000   0.2349
  -6.750  -0.9271   0.05472   0.04599  -0.0061   1.0000   0.2403
  -6.500  -0.9147   0.05343   0.04477  -0.0048   1.0000   0.2464
  -6.250  -0.9035   0.05221   0.04345  -0.0035   1.0000   0.2537
  -6.000  -0.8960   0.05018   0.04101  -0.0021   1.0000   0.2613
  -5.750  -0.8806   0.04953   0.04053  -0.0010   1.0000   0.2694
  -5.500  -0.8702   0.04801   0.03859   0.0001   1.0000   0.2795
  -5.250  -0.8541   0.04741   0.03821   0.0012   1.0000   0.2885
  -5.000  -0.8410   0.04629   0.03684   0.0022   1.0000   0.3004
  -4.750  -0.8254   0.04580   0.03649   0.0033   1.0000   0.3118
  -4.500  -0.8105   0.04509   0.03575   0.0043   1.0000   0.3251
  -4.250  -0.7956   0.04442   0.03494   0.0052   1.0000   0.3407
  -4.000  -0.7798   0.04409   0.03475   0.0063   1.0000   0.3564
  -3.750  -0.7642   0.04378   0.03455   0.0074   1.0000   0.3736
  -3.500  -0.7487   0.04351   0.03438   0.0085   1.0000   0.3931
  -3.250  -0.7331   0.04333   0.03430   0.0096   1.0000   0.4148
  -3.000  -0.7178   0.04325   0.03432   0.0109   1.0000   0.4395
  -2.750  -0.7027   0.04323   0.03441   0.0122   1.0000   0.4673
  -2.500  -0.6881   0.04349   0.03492   0.0140   1.0000   0.4945
  -2.250  -0.6598   0.04498   0.03659   0.0134   0.9934   0.5336
  -2.000  -0.6347   0.04638   0.03816   0.0137   0.9852   0.5735
  -1.750  -0.6079   0.04875   0.04074   0.0145   0.9773   0.6114
  -1.500  -0.5858   0.05030   0.04243   0.0161   0.9666   0.6474
  -1.250  -0.5695   0.05147   0.04361   0.0184   0.9578   0.6837
  -1.000  -0.5440   0.05441   0.04662   0.0203   0.9493   0.7162
  -0.750  -0.5327   0.05488   0.04710   0.0238   0.9382   0.7465
  -0.500  -0.5163   0.05654   0.04873   0.0265   0.9314   0.7773
  -0.250  -0.4979   0.05785   0.05000   0.0291   0.9209   0.8057
   0.000  -0.4801   0.05930   0.05138   0.0312   0.9144   0.8365
   0.250  -0.4494   0.06092   0.05294   0.0310   0.9036   0.8639
   0.500  -0.3985   0.06411   0.05600   0.0264   0.8979   0.8900
   0.750  -0.3462   0.06615   0.05793   0.0207   0.8873   0.9125
   1.000  -0.2449   0.07208   0.06367   0.0054   0.8810   0.9337
   1.250  -0.1942   0.07307   0.06458  -0.0017   0.8701   0.9497
   1.500  -0.0966   0.07797   0.06934  -0.0174   0.8626   0.9683
   1.750  -0.0513   0.07904   0.07035  -0.0244   0.8525   0.9835
   2.000   0.0288   0.08271   0.07391  -0.0377   0.8438   1.0000
   2.250   0.0206   0.08240   0.07353  -0.0349   0.8377   1.0000
   2.500   0.0215   0.08206   0.07311  -0.0332   0.8264   1.0000
   2.750   0.0439   0.08464   0.07557  -0.0349   0.8208   1.0000
   3.000   0.0164   0.08191   0.07281  -0.0287   0.8101   1.0000
   3.250   0.0285   0.08290   0.07370  -0.0284   0.8024   1.0000
   3.500   0.0238   0.08321   0.07393  -0.0257   0.7975   1.0000
   3.750   0.0150   0.08209   0.07274  -0.0221   0.7857   1.0000
   4.000   0.0333   0.08418   0.07473  -0.0223   0.7795   1.0000
   4.250   0.0093   0.08223   0.07273  -0.0166   0.7714   1.0000
   4.500   0.0163   0.08270   0.07311  -0.0150   0.7622   1.0000
   4.750   0.0447   0.08645   0.07671  -0.0165   0.7575   1.0000
   5.000   0.0204   0.08353   0.07375  -0.0111   0.7465   1.0000
   5.250   0.0451   0.08580   0.07592  -0.0123   0.7392   1.0000
   5.500   0.0549   0.08743   0.07747  -0.0119   0.7343   1.0000
   5.750   0.0607   0.08753   0.07752  -0.0108   0.7226   1.0000
   6.000   0.0962   0.09137   0.08127  -0.0134   0.7168   1.0000
   6.250   0.0873   0.09075   0.08062  -0.0110   0.7084   1.0000
   6.500   0.1104   0.09286   0.08268  -0.0121   0.6994   1.0000
   6.750   0.1423   0.09709   0.08683  -0.0144   0.6948   1.0000
   7.000   0.1324   0.09585   0.08559  -0.0119   0.6835   1.0000
   7.250   0.1653   0.09938   0.08907  -0.0141   0.6767   1.0000
   7.500   0.1627   0.09993   0.08961  -0.0129   0.6693   1.0000
   7.750   0.1822   0.10190   0.09155  -0.0136   0.6596   1.0000
   8.250   0.2046   0.10549   0.09511  -0.0139   0.6440   1.0000
   8.500   0.2361   0.10909   0.09869  -0.0159   0.6369   1.0000
   8.750   0.2347   0.11012   0.09972  -0.0151   0.6302   1.0000
   9.000   0.2519   0.11207   0.10167  -0.0157   0.6201   1.0000
   9.250   0.2909   0.11757   0.10714  -0.0185   0.6153   1.0000
   9.500   0.2728   0.11605   0.10565  -0.0163   0.6048   1.0000
   9.750   0.3036   0.11981   0.10941  -0.0181   0.5976   1.0000
  10.000   0.3008   0.12090   0.11052  -0.0176   0.5907   1.0000
  10.250   0.3177   0.12308   0.11271  -0.0183   0.5811   1.0000
  10.500   0.3541   0.12862   0.11824  -0.0207   0.5763   1.0000
  10.750   0.3372   0.12732   0.11698  -0.0192   0.5657   1.0000
  11.000   0.3672   0.13128   0.12096  -0.0209   0.5589   1.0000
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