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=500,000 Ncrit=5


Details Polar file
Airfoil: FX 61-184 AIRFOIL (fx61184-il)
Reynolds number: 500,000
Max Cl/Cd: 100.71 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61184-il-500000-n5.txt
Download as CSV file: xf-fx61184-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -0.6957   0.12446   0.12149  -0.0476   1.0000   0.0073
 -18.250  -0.7329   0.11243   0.10926  -0.0539   1.0000   0.0073
 -18.000  -0.7594   0.10310   0.09976  -0.0588   1.0000   0.0073
 -17.750  -0.7773   0.09573   0.09226  -0.0628   1.0000   0.0073
 -17.500  -0.7936   0.08894   0.08534  -0.0665   1.0000   0.0074
 -17.250  -0.8019   0.08367   0.07999  -0.0694   1.0000   0.0075
 -17.000  -0.8143   0.07800   0.07418  -0.0722   1.0000   0.0075
 -16.750  -0.8210   0.07339   0.06947  -0.0745   1.0000   0.0076
 -16.500  -0.8257   0.06922   0.06520  -0.0765   1.0000   0.0077
 -16.250  -0.8296   0.06535   0.06122  -0.0782   1.0000   0.0077
 -16.000  -0.8326   0.06175   0.05753  -0.0796   1.0000   0.0078
 -15.750  -0.8311   0.05882   0.05453  -0.0808   1.0000   0.0080
 -15.500  -0.8279   0.05578   0.05140  -0.0824   0.9997   0.0081
 -15.250  -0.8082   0.05225   0.04774  -0.0869   0.9417   0.0084
 -15.000  -0.7693   0.04817   0.04340  -0.0971   0.9157   0.0087
 -14.750  -0.7217   0.04484   0.03977  -0.1078   0.8917   0.0092
 -14.500  -0.6896   0.04247   0.03709  -0.1139   0.8609   0.0096
 -14.250  -0.6757   0.04033   0.03476  -0.1162   0.8403   0.0097
 -14.000  -0.6639   0.03859   0.03288  -0.1174   0.8261   0.0099
 -13.750  -0.6487   0.03730   0.03149  -0.1184   0.8155   0.0104
 -13.500  -0.6355   0.03600   0.03008  -0.1189   0.8067   0.0107
 -13.250  -0.6249   0.03454   0.02850  -0.1191   0.7994   0.0109
 -13.000  -0.6128   0.03330   0.02717  -0.1192   0.7930   0.0111
 -12.750  -0.5975   0.03235   0.02612  -0.1194   0.7876   0.0117
 -12.500  -0.5849   0.03122   0.02488  -0.1192   0.7830   0.0120
 -12.250  -0.5711   0.03020   0.02378  -0.1191   0.7784   0.0123
 -12.000  -0.5598   0.02906   0.02260  -0.1188   0.7739   0.0128
 -11.500  -0.5335   0.02711   0.02053  -0.1181   0.7661   0.0134
 -11.250  -0.5175   0.02636   0.01974  -0.1179   0.7624   0.0140
 -11.000  -0.5034   0.02550   0.01882  -0.1174   0.7589   0.0144
 -10.750  -0.4881   0.02474   0.01799  -0.1169   0.7557   0.0149
 -10.500  -0.4733   0.02398   0.01714  -0.1163   0.7527   0.0153
 -10.250  -0.4620   0.02301   0.01615  -0.1155   0.7494   0.0158
 -10.000  -0.4492   0.02216   0.01528  -0.1146   0.7461   0.0163
  -9.750  -0.4355   0.02140   0.01448  -0.1138   0.7430   0.0167
  -9.500  -0.4213   0.02068   0.01372  -0.1130   0.7400   0.0173
  -9.000  -0.3937   0.01926   0.01220  -0.1110   0.7341   0.0183
  -8.750  -0.3803   0.01856   0.01146  -0.1099   0.7311   0.0188
  -8.500  -0.3684   0.01786   0.01073  -0.1085   0.7281   0.0195
  -8.250  -0.3597   0.01720   0.01006  -0.1066   0.7252   0.0205
  -8.000  -0.3455   0.01661   0.00943  -0.1056   0.7225   0.0214
  -7.750  -0.3277   0.01603   0.00879  -0.1052   0.7199   0.0225
  -7.500  -0.3076   0.01549   0.00821  -0.1051   0.7174   0.0236
  -7.250  -0.2872   0.01493   0.00765  -0.1050   0.7146   0.0256
  -7.000  -0.2647   0.01452   0.00720  -0.1049   0.7118   0.0278
  -6.750  -0.2415   0.01410   0.00677  -0.1048   0.7091   0.0313
  -6.500  -0.2172   0.01375   0.00639  -0.1049   0.7065   0.0359
  -6.250  -0.1923   0.01339   0.00602  -0.1051   0.7041   0.0431
  -6.000  -0.1669   0.01301   0.00568  -0.1054   0.7014   0.0527
  -5.750  -0.1411   0.01261   0.00534  -0.1057   0.6986   0.0667
  -5.500  -0.1152   0.01213   0.00496  -0.1062   0.6957   0.0941
  -5.250  -0.0892   0.01144   0.00450  -0.1070   0.6930   0.1522
  -5.000  -0.0619   0.01045   0.00390  -0.1086   0.6905   0.2558
  -4.750  -0.0317   0.00937   0.00328  -0.1108   0.6880   0.3838
  -4.500  -0.0009   0.00886   0.00311  -0.1122   0.6852   0.4683
  -4.250   0.0293   0.00879   0.00312  -0.1129   0.6825   0.5049
  -4.000   0.0592   0.00883   0.00319  -0.1133   0.6795   0.5317
  -3.750   0.0889   0.00894   0.00327  -0.1137   0.6766   0.5488
  -3.500   0.1189   0.00899   0.00323  -0.1142   0.6739   0.5569
  -3.250   0.1483   0.00903   0.00324  -0.1146   0.6712   0.5610
  -3.000   0.1779   0.00905   0.00323  -0.1150   0.6680   0.5648
  -2.750   0.2076   0.00905   0.00319  -0.1155   0.6645   0.5685
  -2.500   0.2374   0.00906   0.00311  -0.1160   0.6611   0.5715
  -2.250   0.2665   0.00907   0.00309  -0.1163   0.6580   0.5737
  -2.000   0.2958   0.00908   0.00308  -0.1167   0.6549   0.5759
  -1.750   0.3252   0.00910   0.00309  -0.1171   0.6512   0.5784
  -1.500   0.3545   0.00911   0.00308  -0.1175   0.6474   0.5809
  -1.250   0.3838   0.00913   0.00305  -0.1179   0.6439   0.5834
  -1.000   0.4133   0.00916   0.00301  -0.1183   0.6406   0.5857
  -0.750   0.4429   0.00916   0.00300  -0.1188   0.6366   0.5877
  -0.500   0.4717   0.00916   0.00301  -0.1191   0.6322   0.5893
  -0.250   0.5005   0.00918   0.00301  -0.1194   0.6281   0.5908
   0.000   0.5294   0.00921   0.00303  -0.1197   0.6239   0.5925
   0.250   0.5583   0.00923   0.00306  -0.1201   0.6188   0.5942
   0.500   0.5870   0.00927   0.00307  -0.1204   0.6141   0.5959
   0.750   0.6157   0.00931   0.00309  -0.1206   0.6097   0.5978
   1.000   0.6446   0.00934   0.00312  -0.1210   0.6046   0.5996
   1.250   0.6733   0.00939   0.00315  -0.1213   0.5994   0.6013
   1.750   0.7304   0.00948   0.00322  -0.1219   0.5892   0.6044
   2.000   0.7584   0.00953   0.00329  -0.1221   0.5832   0.6058
   2.250   0.7862   0.00960   0.00335  -0.1222   0.5773   0.6072
   2.500   0.8141   0.00966   0.00344  -0.1224   0.5704   0.6086
   3.000   0.8694   0.00983   0.00361  -0.1226   0.5575   0.6117
   3.250   0.8964   0.00994   0.00370  -0.1226   0.5500   0.6134
   3.500   0.9236   0.01004   0.00381  -0.1227   0.5417   0.6151
   3.750   0.9496   0.01019   0.00391  -0.1225   0.5319   0.6167
   4.000   0.9762   0.01031   0.00404  -0.1225   0.5219   0.6181
   4.250   1.0026   0.01046   0.00416  -0.1224   0.5140   0.6195
   4.500   1.0289   0.01058   0.00431  -0.1223   0.5057   0.6208
   4.750   1.0547   0.01073   0.00448  -0.1221   0.4974   0.6222
   5.000   1.0801   0.01089   0.00466  -0.1219   0.4887   0.6237
   5.250   1.1056   0.01105   0.00484  -0.1217   0.4805   0.6253
   5.500   1.1297   0.01127   0.00505  -0.1212   0.4705   0.6270
   5.750   1.1541   0.01146   0.00526  -0.1208   0.4589   0.6286
   6.000   1.1773   0.01170   0.00549  -0.1201   0.4463   0.6302
   6.250   1.1996   0.01197   0.00575  -0.1194   0.4331   0.6318
   6.500   1.2211   0.01226   0.00602  -0.1185   0.4197   0.6333
   6.750   1.2415   0.01259   0.00631  -0.1174   0.4058   0.6349
   7.000   1.2605   0.01295   0.00664  -0.1161   0.3900   0.6363
   7.250   1.2769   0.01336   0.00702  -0.1143   0.3712   0.6378
   7.500   1.2874   0.01385   0.00746  -0.1115   0.3499   0.6395
   7.750   1.2960   0.01447   0.00800  -0.1084   0.3277   0.6412
   8.000   1.3038   0.01517   0.00862  -0.1054   0.3041   0.6430
   8.250   1.3081   0.01606   0.00939  -0.1020   0.2793   0.6447
   8.500   1.3101   0.01710   0.01032  -0.0985   0.2535   0.6464
   8.750   1.3132   0.01820   0.01133  -0.0954   0.2312   0.6481
   9.000   1.3169   0.01938   0.01244  -0.0927   0.2116   0.6498
   9.250   1.3223   0.02059   0.01359  -0.0905   0.1951   0.6514
   9.500   1.3288   0.02181   0.01477  -0.0885   0.1811   0.6530
   9.750   1.3364   0.02304   0.01600  -0.0868   0.1687   0.6547
  10.000   1.3442   0.02430   0.01727  -0.0852   0.1571   0.6565
  10.250   1.3511   0.02569   0.01864  -0.0836   0.1448   0.6585
  10.500   1.3569   0.02719   0.02012  -0.0821   0.1318   0.6606
  10.750   1.3623   0.02878   0.02167  -0.0806   0.1193   0.6626
  11.000   1.3666   0.03048   0.02334  -0.0791   0.1065   0.6645
  11.250   1.3708   0.03226   0.02508  -0.0778   0.0946   0.6663
  11.500   1.3736   0.03418   0.02696  -0.0764   0.0820   0.6680
  11.750   1.3775   0.03608   0.02884  -0.0752   0.0711   0.6697
  12.000   1.3810   0.03806   0.03082  -0.0741   0.0614   0.6715
  12.250   1.3852   0.04005   0.03282  -0.0731   0.0535   0.6733
  12.500   1.3898   0.04208   0.03487  -0.0723   0.0475   0.6754
  12.750   1.3949   0.04413   0.03693  -0.0716   0.0418   0.6776
  13.000   1.4009   0.04616   0.03901  -0.0710   0.0381   0.6800
  13.250   1.4067   0.04826   0.04114  -0.0705   0.0348   0.6824
  13.500   1.4124   0.05043   0.04336  -0.0701   0.0322   0.6846
  13.750   1.4188   0.05259   0.04560  -0.0698   0.0301   0.6869
  14.000   1.4239   0.05495   0.04801  -0.0696   0.0279   0.6892
  14.250   1.4290   0.05736   0.05048  -0.0694   0.0260   0.6916
  14.500   1.4348   0.05973   0.05293  -0.0694   0.0244   0.6942
  14.750   1.4397   0.06226   0.05553  -0.0694   0.0229   0.6968
  15.000   1.4433   0.06502   0.05835  -0.0695   0.0216   0.6994
  15.250   1.4487   0.06760   0.06102  -0.0696   0.0207   0.7020
  15.500   1.4534   0.07031   0.06383  -0.0699   0.0196   0.7048
  15.750   1.4570   0.07322   0.06683  -0.0703   0.0186   0.7079
  16.000   1.4597   0.07628   0.06997  -0.0707   0.0176   0.7112
  16.250   1.4626   0.07940   0.07317  -0.0713   0.0167   0.7146
  16.500   1.4660   0.08249   0.07636  -0.0719   0.0159   0.7182
  16.750   1.4687   0.08570   0.07968  -0.0726   0.0151   0.7223
  17.000   1.4700   0.08918   0.08325  -0.0735   0.0144   0.7266
  17.250   1.4702   0.09286   0.08702  -0.0745   0.0136   0.7309
  17.500   1.4723   0.09632   0.09059  -0.0755   0.0130   0.7355
  17.750   1.4735   0.09996   0.09435  -0.0767   0.0123   0.7406
  18.000   1.4736   0.10379   0.09828  -0.0779   0.0115   0.7459
  18.250   1.4729   0.10779   0.10238  -0.0794   0.0108   0.7514
  18.500   1.4729   0.11172   0.10644  -0.0809   0.0101   0.7581
  18.750   1.4723   0.11580   0.11063  -0.0825   0.0093   0.7653
<< Back to FX 61-184 AIRFOIL (fx61184-il)

Polar data table (+)

Polar graphs


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