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

FX 61-184 AIRFOIL (fx61184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 61-184 AIRFOIL (fx61184-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.08 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61184-il-1000000.txt
Download as CSV file: xf-fx61184-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-184 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
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -0.6955   0.13836   0.13623  -0.0393   1.0000   0.0070
 -19.000  -0.7620   0.11994   0.11754  -0.0487   1.0000   0.0068
 -18.750  -0.7851   0.11104   0.10850  -0.0535   1.0000   0.0070
 -18.500  -0.8193   0.10079   0.09809  -0.0589   1.0000   0.0067
 -18.250  -0.8356   0.09391   0.09107  -0.0626   1.0000   0.0068
 -18.000  -0.8557   0.08672   0.08374  -0.0664   1.0000   0.0068
 -17.750  -0.8615   0.08193   0.07885  -0.0689   1.0000   0.0069
 -17.500  -0.8741   0.07638   0.07317  -0.0717   1.0000   0.0070
 -17.250  -0.8705   0.07321   0.06992  -0.0733   1.0000   0.0071
 -17.000  -0.8804   0.06839   0.06498  -0.0755   1.0000   0.0071
 -16.750  -0.8860   0.06434   0.06082  -0.0772   1.0000   0.0072
 -16.500  -0.9045   0.05890   0.05524  -0.0791   1.0000   0.0074
 -16.250  -0.9061   0.05572   0.05197  -0.0802   1.0000   0.0075
 -16.000  -0.9090   0.05253   0.04870  -0.0810   1.0000   0.0075
 -15.750  -0.9042   0.05024   0.04639  -0.0817   1.0000   0.0078
 -15.500  -0.9000   0.04799   0.04410  -0.0821   1.0000   0.0079
 -15.250  -0.8920   0.04621   0.04228  -0.0825   1.0000   0.0082
 -15.000  -0.8746   0.04315   0.03914  -0.0859   0.9615   0.0083
 -14.750  -0.8177   0.04063   0.03645  -0.0968   0.9280   0.0089
 -14.500  -0.7634   0.03852   0.03401  -0.1066   0.8827   0.0093
 -14.250  -0.7280   0.03661   0.03185  -0.1126   0.8527   0.0095
 -14.000  -0.7179   0.03413   0.02916  -0.1149   0.8332   0.0100
 -13.750  -0.6992   0.03286   0.02782  -0.1165   0.8209   0.0103
 -13.500  -0.6821   0.03168   0.02655  -0.1175   0.8119   0.0106
 -13.250  -0.6673   0.03041   0.02518  -0.1182   0.8042   0.0109
 -13.000  -0.6520   0.02931   0.02400  -0.1187   0.7980   0.0111
 -12.750  -0.6337   0.02848   0.02311  -0.1192   0.7921   0.0116
 -12.500  -0.6175   0.02751   0.02204  -0.1194   0.7869   0.0119
 -12.250  -0.5994   0.02675   0.02121  -0.1196   0.7826   0.0122
 -12.000  -0.5906   0.02541   0.01981  -0.1191   0.7783   0.0126
 -11.750  -0.5785   0.02432   0.01867  -0.1188   0.7742   0.0130
 -11.500  -0.5634   0.02345   0.01774  -0.1187   0.7701   0.0134
 -11.250  -0.5467   0.02273   0.01700  -0.1184   0.7669   0.0138
 -11.000  -0.5323   0.02190   0.01613  -0.1179   0.7635   0.0140
 -10.750  -0.5158   0.02121   0.01540  -0.1175   0.7602   0.0145
 -10.500  -0.4995   0.02054   0.01468  -0.1170   0.7568   0.0149
 -10.250  -0.4796   0.02007   0.01415  -0.1169   0.7530   0.0156
 -10.000  -0.4716   0.01898   0.01302  -0.1155   0.7503   0.0160
  -9.750  -0.4599   0.01812   0.01215  -0.1144   0.7474   0.0164
  -9.500  -0.4461   0.01740   0.01141  -0.1134   0.7445   0.0170
  -9.250  -0.4276   0.01697   0.01096  -0.1128   0.7416   0.0178
  -9.000  -0.4139   0.01632   0.01026  -0.1117   0.7385   0.0183
  -8.750  -0.3996   0.01579   0.00970  -0.1104   0.7357   0.0188
  -8.500  -0.3875   0.01528   0.00916  -0.1089   0.7333   0.0191
  -8.250  -0.3769   0.01425   0.00809  -0.1080   0.7305   0.0201
  -8.000  -0.3572   0.01364   0.00745  -0.1080   0.7278   0.0210
  -7.750  -0.3351   0.01321   0.00699  -0.1078   0.7251   0.0219
  -7.500  -0.3114   0.01287   0.00660  -0.1078   0.7224   0.0229
  -7.250  -0.2875   0.01248   0.00616  -0.1079   0.7197   0.0244
  -7.000  -0.2634   0.01205   0.00574  -0.1079   0.7174   0.0268
  -6.750  -0.2378   0.01172   0.00539  -0.1081   0.7150   0.0299
  -6.500  -0.2119   0.01135   0.00503  -0.1083   0.7124   0.0354
  -6.250  -0.1857   0.01095   0.00469  -0.1086   0.7100   0.0461
  -6.000  -0.1589   0.01058   0.00437  -0.1091   0.7074   0.0621
  -5.750  -0.1317   0.01012   0.00403  -0.1098   0.7045   0.0963
  -5.500  -0.1047   0.00926   0.00352  -0.1110   0.7025   0.1803
  -5.250  -0.0755   0.00818   0.00294  -0.1129   0.7002   0.3047
  -5.000  -0.0443   0.00735   0.00250  -0.1147   0.6977   0.4126
  -4.750  -0.0132   0.00698   0.00233  -0.1159   0.6950   0.4762
  -4.500   0.0172   0.00690   0.00228  -0.1166   0.6925   0.5045
  -4.250   0.0475   0.00691   0.00227  -0.1172   0.6897   0.5244
  -4.000   0.0776   0.00694   0.00229  -0.1177   0.6871   0.5381
  -3.750   0.1076   0.00696   0.00231  -0.1182   0.6844   0.5482
  -3.500   0.1376   0.00704   0.00238  -0.1186   0.6815   0.5601
  -3.250   0.1674   0.00712   0.00244  -0.1190   0.6787   0.5669
  -3.000   0.1975   0.00721   0.00246  -0.1195   0.6758   0.5715
  -2.750   0.2271   0.00723   0.00244  -0.1199   0.6725   0.5747
  -2.500   0.2566   0.00723   0.00245  -0.1203   0.6699   0.5775
  -2.250   0.2863   0.00724   0.00246  -0.1208   0.6669   0.5802
  -2.000   0.3160   0.00726   0.00245  -0.1212   0.6638   0.5827
  -1.750   0.3457   0.00728   0.00243  -0.1217   0.6605   0.5849
  -1.500   0.3754   0.00735   0.00242  -0.1221   0.6568   0.5868
  -1.250   0.4050   0.00731   0.00239  -0.1226   0.6537   0.5889
  -1.000   0.4344   0.00728   0.00237  -0.1230   0.6499   0.5911
  -0.750   0.4637   0.00729   0.00238  -0.1234   0.6459   0.5930
  -0.500   0.4928   0.00734   0.00239  -0.1237   0.6419   0.5949
  -0.250   0.5223   0.00735   0.00241  -0.1241   0.6382   0.5968
   0.000   0.5517   0.00736   0.00242  -0.1245   0.6340   0.5987
   0.250   0.5810   0.00739   0.00242  -0.1249   0.6297   0.6004
   0.500   0.6100   0.00745   0.00244  -0.1253   0.6254   0.6018
   0.750   0.6396   0.00747   0.00246  -0.1258   0.6212   0.6031
   1.000   0.6687   0.00745   0.00245  -0.1262   0.6162   0.6049
   1.250   0.6971   0.00748   0.00245  -0.1264   0.6109   0.6066
   1.500   0.7262   0.00749   0.00249  -0.1268   0.6056   0.6081
   1.750   0.7549   0.00753   0.00254  -0.1271   0.5998   0.6097
   2.000   0.7830   0.00761   0.00258  -0.1273   0.5942   0.6112
   2.250   0.8120   0.00764   0.00263  -0.1276   0.5881   0.6127
   2.500   0.8400   0.00771   0.00269  -0.1278   0.5812   0.6143
   2.750   0.8684   0.00777   0.00275  -0.1280   0.5738   0.6159
   3.000   0.8960   0.00787   0.00281  -0.1281   0.5653   0.6174
   3.250   0.9243   0.00794   0.00288  -0.1284   0.5583   0.6186
   3.500   0.9521   0.00804   0.00296  -0.1285   0.5514   0.6196
   3.750   0.9799   0.00809   0.00303  -0.1287   0.5444   0.6214
   4.000   1.0073   0.00818   0.00312  -0.1288   0.5366   0.6231
   4.250   1.0347   0.00828   0.00323  -0.1289   0.5299   0.6247
   4.500   1.0621   0.00838   0.00335  -0.1290   0.5223   0.6262
   4.750   1.0888   0.00851   0.00347  -0.1290   0.5142   0.6276
   5.000   1.1154   0.00865   0.00360  -0.1289   0.5046   0.6291
   5.250   1.1419   0.00878   0.00374  -0.1289   0.4949   0.6306
   5.500   1.1673   0.00897   0.00390  -0.1286   0.4849   0.6321
   5.750   1.1936   0.00912   0.00405  -0.1285   0.4747   0.6335
   6.000   1.2190   0.00930   0.00422  -0.1283   0.4637   0.6348
   6.250   1.2434   0.00953   0.00442  -0.1279   0.4517   0.6360
   6.500   1.2673   0.00974   0.00461  -0.1274   0.4381   0.6382
   6.750   1.2902   0.01000   0.00484  -0.1267   0.4213   0.6399
   7.000   1.3119   0.01031   0.00511  -0.1259   0.4023   0.6414
   7.250   1.3304   0.01076   0.00545  -0.1244   0.3777   0.6429
   7.500   1.3468   0.01127   0.00584  -0.1227   0.3495   0.6445
   7.750   1.3628   0.01177   0.00625  -0.1208   0.3267   0.6462
   8.000   1.3763   0.01227   0.00666  -0.1185   0.3041   0.6478
   8.250   1.3852   0.01284   0.00713  -0.1154   0.2827   0.6493
   8.500   1.3936   0.01350   0.00768  -0.1123   0.2587   0.6508
   8.750   1.3994   0.01428   0.00835  -0.1089   0.2364   0.6521
   9.000   1.4062   0.01504   0.00903  -0.1059   0.2160   0.6544
   9.250   1.4111   0.01592   0.00985  -0.1027   0.1966   0.6564
   9.500   1.4156   0.01691   0.01077  -0.0997   0.1800   0.6581
   9.750   1.4208   0.01796   0.01178  -0.0971   0.1650   0.6599
  10.000   1.4269   0.01906   0.01284  -0.0948   0.1510   0.6617
  10.250   1.4327   0.02028   0.01401  -0.0926   0.1373   0.6635
  10.500   1.4373   0.02165   0.01533  -0.0905   0.1232   0.6653
  10.750   1.4423   0.02307   0.01670  -0.0886   0.1104   0.6669
  11.000   1.4461   0.02464   0.01821  -0.0867   0.0975   0.6683
  11.250   1.4512   0.02617   0.01973  -0.0851   0.0862   0.6708
  11.500   1.4543   0.02790   0.02142  -0.0834   0.0741   0.6730
  11.750   1.4578   0.02965   0.02315  -0.0818   0.0639   0.6752
  12.000   1.4619   0.03142   0.02490  -0.0804   0.0555   0.6773
  12.250   1.4651   0.03329   0.02675  -0.0790   0.0479   0.6793
  12.500   1.4689   0.03518   0.02863  -0.0778   0.0416   0.6813
  12.750   1.4744   0.03700   0.03045  -0.0768   0.0365   0.6832
  13.000   1.4790   0.03895   0.03242  -0.0758   0.0326   0.6852
  13.250   1.4866   0.04069   0.03422  -0.0751   0.0303   0.6878
  13.500   1.4920   0.04270   0.03626  -0.0744   0.0279   0.6903
  13.750   1.4988   0.04463   0.03824  -0.0738   0.0261   0.6928
  14.000   1.5069   0.04647   0.04014  -0.0734   0.0248   0.6955
  14.250   1.5127   0.04860   0.04231  -0.0729   0.0233   0.6981
  14.500   1.5175   0.05088   0.04463  -0.0725   0.0218   0.7006
  14.750   1.5246   0.05300   0.04684  -0.0723   0.0210   0.7040
  15.000   1.5322   0.05510   0.04901  -0.0721   0.0201   0.7072
  15.250   1.5382   0.05740   0.05136  -0.0720   0.0191   0.7105
  15.500   1.5423   0.05997   0.05399  -0.0720   0.0180   0.7138
  15.750   1.5463   0.06262   0.05670  -0.0720   0.0170   0.7170
  16.000   1.5530   0.06502   0.05919  -0.0722   0.0164   0.7211
  16.250   1.5584   0.06760   0.06184  -0.0724   0.0155   0.7254
  16.500   1.5619   0.07045   0.06474  -0.0727   0.0145   0.7298
  16.750   1.5637   0.07361   0.06797  -0.0732   0.0134   0.7343
  17.000   1.5688   0.07636   0.07082  -0.0736   0.0124   0.7400
  17.250   1.5698   0.07973   0.07425  -0.0743   0.0111   0.7458
  17.500   1.5711   0.08313   0.07773  -0.0750   0.0097   0.7524
  17.750   1.5698   0.08693   0.08159  -0.0759   0.0081   0.7602
  18.000   1.5683   0.09085   0.08560  -0.0769   0.0064   0.7690
  18.250   1.5655   0.09507   0.08991  -0.0781   0.0053   0.7799
  18.750   1.5597   0.10378   0.09887  -0.0811   0.0042   0.8136
  19.000   1.5573   0.10815   0.10341  -0.0827   0.0039   0.8476
  19.250   1.5471   0.11161   0.10715  -0.0823   0.0038   1.0000
<< Back to FX 61-184 AIRFOIL (fx61184-il)

Polar data table (+)

Polar graphs


<< Back to FX 61-184 AIRFOIL (fx61184-il)