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FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 74-130 WP1 (fx74130wp1-il)
Reynolds number: 200,000
Max Cl/Cd: 71.21 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp1-il-200000-n5.txt
Download as CSV file: xf-fx74130wp1-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-130 WP1                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1309   0.09252   0.08811  -0.1189   0.8656   0.0260
 -10.250  -0.1289   0.08895   0.08455  -0.1212   0.8634   0.0262
  -9.250  -0.1257   0.07256   0.06819  -0.1263   0.8554   0.0181
  -9.000  -0.1269   0.06904   0.06471  -0.1279   0.8528   0.0174
  -8.750  -0.1322   0.06476   0.06045  -0.1309   0.8500   0.0167
  -8.500  -0.1432   0.06030   0.05596  -0.1333   0.8472   0.0161
  -8.250  -0.1590   0.05672   0.05231  -0.1332   0.8443   0.0156
  -7.750  -0.1840   0.04615   0.04129  -0.1310   0.8379   0.0134
  -7.500  -0.1840   0.04292   0.03786  -0.1296   0.8354   0.0134
  -7.250  -0.1797   0.03988   0.03456  -0.1282   0.8333   0.0133
  -7.000  -0.1728   0.03656   0.03087  -0.1266   0.8316   0.0134
  -6.750  -0.1645   0.03362   0.02753  -0.1249   0.8296   0.0137
  -6.500  -0.1523   0.03189   0.02567  -0.1239   0.8271   0.0144
  -6.250  -0.1346   0.03095   0.02462  -0.1233   0.8248   0.0154
  -6.000  -0.1175   0.02885   0.02220  -0.1221   0.8227   0.0157
  -5.750  -0.0984   0.02649   0.01942  -0.1210   0.8209   0.0155
  -5.500  -0.0766   0.02448   0.01702  -0.1201   0.8195   0.0155
  -5.250  -0.0528   0.02288   0.01510  -0.1195   0.8182   0.0156
  -5.000  -0.0278   0.02156   0.01351  -0.1191   0.8170   0.0158
  -4.750  -0.0056   0.02058   0.01239  -0.1181   0.8148   0.0163
  -4.500   0.0164   0.01975   0.01144  -0.1172   0.8123   0.0170
  -4.250   0.0392   0.01900   0.01061  -0.1164   0.8101   0.0177
  -4.000   0.0627   0.01841   0.00993  -0.1158   0.8083   0.0188
  -3.750   0.0860   0.01779   0.00930  -0.1154   0.8067   0.0212
  -3.500   0.1109   0.01737   0.00885  -0.1152   0.8052   0.0238
  -3.250   0.1365   0.01692   0.00830  -0.1149   0.8039   0.0261
  -3.000   0.1624   0.01644   0.00777  -0.1149   0.8027   0.0310
  -2.750   0.1821   0.01628   0.00762  -0.1138   0.7994   0.0408
  -2.500   0.2042   0.01598   0.00743  -0.1131   0.7968   0.0722
  -2.250   0.2253   0.01510   0.00728  -0.1130   0.7946   0.2555
  -2.000   0.2329   0.01387   0.00785  -0.1090   0.7925   0.6874
  -1.750   0.2552   0.01433   0.00831  -0.1072   0.7910   0.7825
  -1.500   0.2768   0.01476   0.00865  -0.1051   0.7896   0.8175
  -1.250   0.2888   0.01522   0.00912  -0.1007   0.7874   0.8431
  -1.000   0.2965   0.01567   0.00959  -0.0963   0.7830   0.8613
  -0.750   0.3128   0.01583   0.00971  -0.0937   0.7804   0.8705
  -0.500   0.3388   0.01588   0.00965  -0.0936   0.7785   0.8767
  -0.250   0.3639   0.01585   0.00956  -0.0930   0.7769   0.8798
   0.000   0.3915   0.01583   0.00946  -0.0932   0.7756   0.8824
   0.250   0.4204   0.01582   0.00938  -0.0936   0.7746   0.8848
   0.500   0.4322   0.01624   0.00983  -0.0914   0.7690   0.8885
   0.750   0.4575   0.01636   0.00991  -0.0914   0.7662   0.8906
   1.000   0.4834   0.01639   0.00991  -0.0914   0.7643   0.8921
   1.250   0.5116   0.01638   0.00987  -0.0917   0.7627   0.8935
   1.500   0.5413   0.01634   0.00981  -0.0923   0.7615   0.8948
   1.750   0.5721   0.01629   0.00974  -0.0931   0.7604   0.8961
   2.250   0.6061   0.01684   0.01037  -0.0902   0.7504   0.9005
   2.500   0.6373   0.01676   0.01030  -0.0912   0.7487   0.9014
   2.750   0.6698   0.01666   0.01020  -0.0923   0.7474   0.9022
   3.250   0.7054   0.01721   0.01087  -0.0897   0.7374   0.9058
   3.500   0.7361   0.01707   0.01078  -0.0904   0.7355   0.9065
   3.750   0.7695   0.01686   0.01060  -0.0916   0.7339   0.9071
   4.250   0.8058   0.01710   0.01102  -0.0887   0.7227   0.9109
   4.500   0.8417   0.01668   0.01066  -0.0901   0.7204   0.9115
   4.750   0.8495   0.01701   0.01107  -0.0869   0.7118   0.9139
   5.000   0.8841   0.01652   0.01066  -0.0880   0.7078   0.9145
   5.250   0.8957   0.01662   0.01087  -0.0853   0.6987   0.9167
   5.500   0.9341   0.01587   0.01020  -0.0869   0.6926   0.9172
   5.750   0.9470   0.01589   0.01031  -0.0842   0.6804   0.9195
   6.000   0.9686   0.01563   0.01012  -0.0830   0.6668   0.9216
   6.250   0.9917   0.01531   0.00986  -0.0819   0.6464   0.9235
   6.500   1.0193   0.01487   0.00938  -0.0814   0.6114   0.9249
   6.750   1.0440   0.01466   0.00871  -0.0802   0.5259   0.9262
   7.000   1.0372   0.01583   0.00938  -0.0747   0.4480   0.9303
   7.250   1.0300   0.01721   0.01043  -0.0697   0.3874   0.9348
   7.500   1.0231   0.01875   0.01168  -0.0651   0.3278   0.9402
   8.000   1.0220   0.02176   0.01418  -0.0588   0.2200   0.9554
   8.250   1.0263   0.02326   0.01542  -0.0567   0.1684   0.9711
   8.500   1.0316   0.02471   0.01662  -0.0547   0.1227   1.0000
   8.750   1.0401   0.02616   0.01787  -0.0532   0.0874   1.0000
   9.000   1.0514   0.02744   0.01906  -0.0521   0.0651   1.0000
   9.250   1.0630   0.02874   0.02029  -0.0509   0.0509   1.0000
   9.500   1.0759   0.02995   0.02155  -0.0499   0.0426   1.0000
   9.750   1.0881   0.03123   0.02286  -0.0488   0.0371   1.0000
  10.000   1.1013   0.03245   0.02417  -0.0479   0.0335   1.0000
  10.250   1.1122   0.03386   0.02563  -0.0468   0.0304   1.0000
  10.500   1.1222   0.03536   0.02722  -0.0456   0.0281   1.0000
  10.750   1.1350   0.03666   0.02863  -0.0447   0.0258   1.0000
  11.000   1.1462   0.03811   0.03018  -0.0438   0.0240   1.0000
  11.250   1.1561   0.03971   0.03187  -0.0427   0.0225   1.0000
  11.500   1.1621   0.04173   0.03393  -0.0414   0.0208   1.0000
  11.750   1.1755   0.04308   0.03544  -0.0407   0.0192   1.0000
  12.000   1.1864   0.04473   0.03721  -0.0399   0.0181   1.0000
  12.250   1.1970   0.04638   0.03896  -0.0391   0.0167   1.0000
  12.500   1.2063   0.04816   0.04080  -0.0384   0.0155   1.0000
  12.750   1.2139   0.05030   0.04303  -0.0375   0.0144   1.0000
  13.000   1.2249   0.05209   0.04502  -0.0368   0.0135   1.0000
  13.250   1.2347   0.05411   0.04723  -0.0360   0.0127   1.0000
  13.500   1.2431   0.05626   0.04955  -0.0353   0.0121   1.0000
  13.750   1.2503   0.05854   0.05198  -0.0347   0.0114   1.0000
  14.000   1.2561   0.06098   0.05456  -0.0342   0.0110   1.0000
  14.250   1.2600   0.06363   0.05733  -0.0338   0.0106   1.0000
  14.500   1.2611   0.06690   0.06074  -0.0332   0.0101   1.0000
  14.750   1.2625   0.07007   0.06419  -0.0329   0.0098   1.0000
  15.000   1.2616   0.07359   0.06799  -0.0327   0.0093   1.0000
  15.250   1.2583   0.07750   0.07216  -0.0328   0.0090   1.0000
  15.500   1.2530   0.08172   0.07663  -0.0331   0.0086   1.0000
  15.750   1.2458   0.08635   0.08151  -0.0339   0.0084   1.0000
  16.000   1.2365   0.09146   0.08686  -0.0350   0.0082   1.0000
  16.250   1.2250   0.09714   0.09278  -0.0366   0.0081   1.0000
  16.500   1.2117   0.10335   0.09923  -0.0389   0.0080   1.0000
  16.750   1.1966   0.11019   0.10631  -0.0418   0.0080   1.0000
  17.000   1.1801   0.11771   0.11407  -0.0456   0.0079   1.0000
  17.250   1.1610   0.12628   0.12287  -0.0504   0.0080   1.0000
  17.500   1.1388   0.13626   0.13308  -0.0565   0.0080   1.0000
  17.750   1.1125   0.14828   0.14533  -0.0643   0.0082   1.0000
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