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

FX 84-W-218 (fx84w218-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 84-W-218 (fx84w218-il)
Reynolds number: 100,000
Max Cl/Cd: 7.06 at α=11.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx84w218-il-100000.txt
Download as CSV file: xf-fx84w218-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.1893   0.14289   0.13759  -0.0677   0.9773   0.1816
 -13.500  -0.2315   0.14054   0.13526  -0.0741   0.9719   0.1898
 -13.250  -0.6058   0.07021   0.06433  -0.1056   0.9694   0.1241
 -13.000  -0.3913   0.09120   0.08571  -0.0982   0.9675   0.1346
 -12.750  -0.5434   0.06720   0.06134  -0.1110   0.9615   0.1304
 -12.500  -0.6269   0.05795   0.05160  -0.1139   0.9520   0.1289
 -12.250  -0.6585   0.05464   0.04802  -0.1127   0.9425   0.1296
 -12.000  -0.6766   0.05167   0.04472  -0.1122   0.9356   0.1313
 -11.750  -0.7080   0.05065   0.04350  -0.1062   0.9244   0.1318
 -11.500  -0.7216   0.04843   0.04086  -0.1038   0.9178   0.1337
 -11.250  -0.7553   0.04813   0.04039  -0.0955   0.9059   0.1341
 -11.000  -0.7206   0.04645   0.03874  -0.0981   0.9025   0.1379
 -10.750  -0.6875   0.04505   0.03725  -0.1005   0.8997   0.1426
 -10.500  -0.7238   0.04531   0.03743  -0.0909   0.8874   0.1429
 -10.250  -0.7165   0.04379   0.03545  -0.0895   0.8826   0.1467
 -10.000  -0.7468   0.04386   0.03543  -0.0809   0.8725   0.1472
  -9.750  -0.7142   0.04295   0.03472  -0.0823   0.8680   0.1518
  -9.500  -0.6876   0.04192   0.03350  -0.0831   0.8641   0.1575
  -9.250  -0.7071   0.04181   0.03320  -0.0761   0.8554   0.1593
  -9.000  -0.6958   0.04112   0.03255  -0.0741   0.8493   0.1631
  -8.750  -0.6675   0.04049   0.03191  -0.0748   0.8454   0.1694
  -8.500  -0.6307   0.03937   0.03064  -0.0769   0.8426   0.1772
  -8.250  -0.6643   0.03977   0.03103  -0.0676   0.8321   0.1777
  -8.000  -0.6437   0.03934   0.03063  -0.0669   0.8270   0.1842
  -7.750  -0.6132   0.03855   0.02972  -0.0678   0.8236   0.1927
  -7.500  -0.5705   0.03792   0.02906  -0.0705   0.8213   0.2037
  -7.250  -0.6132   0.03850   0.02964  -0.0600   0.8100   0.2032
  -7.000  -0.5884   0.03795   0.02915  -0.0599   0.8054   0.2120
  -6.750  -0.5561   0.03745   0.02850  -0.0608   0.8021   0.2240
  -6.500  -0.5117   0.03687   0.02803  -0.0636   0.8000   0.2387
  -6.250  -0.5559   0.03761   0.02877  -0.0533   0.7889   0.2380
  -6.000  -0.5305   0.03718   0.02844  -0.0531   0.7842   0.2502
  -5.750  -0.4960   0.03668   0.02797  -0.0543   0.7810   0.2664
  -5.500  -0.4541   0.03621   0.02759  -0.0565   0.7788   0.2863
  -5.250  -0.4955   0.03712   0.02850  -0.0471   0.7683   0.2866
  -5.000  -0.4722   0.03687   0.02831  -0.0466   0.7634   0.3043
  -4.750  -0.4371   0.03644   0.02800  -0.0476   0.7599   0.3273
  -4.500  -0.3959   0.03604   0.02771  -0.0495   0.7577   0.3557
  -4.250  -0.4336   0.03712   0.02878  -0.0411   0.7476   0.3590
  -4.000  -0.4113   0.03698   0.02880  -0.0404   0.7426   0.3838
  -3.750  -0.3767   0.03668   0.02870  -0.0411   0.7391   0.4163
  -3.500  -0.3347   0.03640   0.02863  -0.0426   0.7368   0.4546
  -3.250  -0.3701   0.03763   0.02988  -0.0351   0.7268   0.4630
  -3.000  -0.3475   0.03772   0.03017  -0.0342   0.7218   0.4956
  -2.750  -0.3118   0.03771   0.03030  -0.0346   0.7183   0.5347
  -2.500  -0.2981   0.03835   0.03106  -0.0325   0.7132   0.5625
  -2.250  -0.3061   0.03929   0.03210  -0.0283   0.7057   0.5825
  -2.000  -0.2820   0.03970   0.03257  -0.0273   0.7008   0.6125
  -1.750  -0.2448   0.03996   0.03286  -0.0274   0.6975   0.6422
  -1.500  -0.2453   0.04103   0.03395  -0.0240   0.6909   0.6620
  -1.250  -0.2434   0.04203   0.03504  -0.0207   0.6844   0.6792
  -1.000  -0.2171   0.04252   0.03555  -0.0195   0.6798   0.7006
  -0.750  -0.1795   0.04285   0.03587  -0.0192   0.6767   0.7216
  -0.500  -0.1940   0.04424   0.03731  -0.0145   0.6688   0.7357
  -0.250  -0.1861   0.04509   0.03815  -0.0120   0.6632   0.7535
   0.000  -0.1590   0.04549   0.03852  -0.0107   0.6589   0.7719
   0.250  -0.1219   0.04573   0.03874  -0.0099   0.6561   0.7880
   0.500  -0.1486   0.04732   0.04040  -0.0044   0.6469   0.8019
   0.750  -0.1371   0.04800   0.04105  -0.0021   0.6420   0.8193
   1.000  -0.1099   0.04826   0.04129  -0.0005   0.6383   0.8355
   1.250  -0.0700   0.04825   0.04122   0.0001   0.6357   0.8511
   1.500  -0.1078   0.05007   0.04313   0.0061   0.6254   0.8666
   1.750  -0.0907   0.05059   0.04362   0.0080   0.6210   0.8837
   2.000  -0.0538   0.05067   0.04364   0.0081   0.6176   0.9008
   2.250  -0.0541   0.05208   0.04507   0.0101   0.6097   0.9174
   2.500  -0.0316   0.05327   0.04626   0.0093   0.6036   0.9329
   2.750   0.0333   0.05414   0.04706   0.0035   0.5993   0.9421
   3.000   0.1074   0.05431   0.04715  -0.0027   0.5966   0.9509
   3.250   0.1103   0.05752   0.05041  -0.0054   0.5849   0.9607
   3.500   0.1739   0.05825   0.05109  -0.0117   0.5805   0.9669
   3.750   0.2493   0.05818   0.05095  -0.0185   0.5778   0.9726
   4.000   0.2492   0.06161   0.05443  -0.0210   0.5659   0.9822
   4.250   0.3062   0.06207   0.05486  -0.0264   0.5614   0.9893
   4.500   0.3747   0.06174   0.05448  -0.0322   0.5588   0.9954
   4.750   0.3409   0.06507   0.05785  -0.0298   0.5472   1.0000
   5.000   0.3433   0.06477   0.05749  -0.0267   0.5428   1.0000
   5.250   0.3606   0.06389   0.05654  -0.0246   0.5401   1.0000
   5.500   0.3867   0.06281   0.05539  -0.0230   0.5383   1.0000
   5.750   0.3017   0.06626   0.05883  -0.0142   0.5248   1.0000
   6.000   0.3340   0.06584   0.05834  -0.0141   0.5215   1.0000
   6.250   0.3785   0.06506   0.05748  -0.0148   0.5195   1.0000
   6.500   0.3340   0.06947   0.06191  -0.0121   0.5060   1.0000
   6.750   0.3738   0.06907   0.06145  -0.0127   0.5026   1.0000
   7.000   0.4212   0.06823   0.06056  -0.0135   0.5006   1.0000
   7.250   0.3806   0.07306   0.06541  -0.0116   0.4867   1.0000
   7.500   0.4227   0.07246   0.06477  -0.0122   0.4836   1.0000
   7.750   0.4704   0.07149   0.06374  -0.0128   0.4817   1.0000
   8.000   0.4295   0.07677   0.06907  -0.0114   0.4673   1.0000
   8.250   0.4727   0.07596   0.06823  -0.0118   0.4645   1.0000
   8.500   0.4440   0.08080   0.07310  -0.0110   0.4522   1.0000
   8.750   0.4794   0.08049   0.07277  -0.0112   0.4479   1.0000
   9.000   0.5238   0.07944   0.07170  -0.0114   0.4456   1.0000
   9.250   0.4898   0.08503   0.07733  -0.0109   0.4321   1.0000
   9.500   0.5289   0.08429   0.07657  -0.0109   0.4287   1.0000
   9.750   0.5746   0.08294   0.07521  -0.0110   0.4267   1.0000
  10.000   0.5360   0.08927   0.08159  -0.0108   0.4124   1.0000
  10.250   0.5781   0.08809   0.08040  -0.0107   0.4096   1.0000
  10.500   0.5493   0.09388   0.08624  -0.0109   0.3969   1.0000
  10.750   0.5833   0.09343   0.08579  -0.0108   0.3930   1.0000
  11.000   0.6280   0.09176   0.08412  -0.0105   0.3908   1.0000
  11.250   0.5903   0.09882   0.09124  -0.0111   0.3770   1.0000
  11.500   0.6299   0.09758   0.09000  -0.0108   0.3740   1.0000
  11.750   0.6754   0.09560   0.08803  -0.0103   0.3723   1.0000
  12.000   0.6324   0.10367   0.09616  -0.0114   0.3577   1.0000
  12.250   0.6752   0.10185   0.09435  -0.0109   0.3554   1.0000
  12.500   0.6356   0.10997   0.10254  -0.0124   0.3422   1.0000
  12.750   0.6748   0.10840   0.10097  -0.0118   0.3389   1.0000
  13.000   0.7201   0.10599   0.09858  -0.0109   0.3371   1.0000
  13.250   0.6758   0.11507   0.10772  -0.0130   0.3229   1.0000
  13.500   0.7185   0.11282   0.10549  -0.0121   0.3205   1.0000
<< Back to FX 84-W-218 (fx84w218-il)

Polar data table (+)

Polar graphs


<< Back to FX 84-W-218 (fx84w218-il)