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FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 74-130 WP1 (fx74130wp1-il)
Reynolds number: 500,000
Max Cl/Cd: 119.3 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp1-il-500000.txt
Download as CSV file: xf-fx74130wp1-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1074   0.08860   0.08541  -0.1223   0.8593   0.0166
 -10.250  -0.1047   0.08525   0.08208  -0.1238   0.8578   0.0168
 -10.000  -0.1017   0.08205   0.07890  -0.1252   0.8561   0.0169
  -9.750  -0.1004   0.07848   0.07536  -0.1270   0.8541   0.0174
  -9.500  -0.1017   0.07410   0.07100  -0.1298   0.8521   0.0183
  -9.250  -0.1025   0.06948   0.06641  -0.1335   0.8499   0.0187
  -9.000  -0.1059   0.06464   0.06158  -0.1376   0.8478   0.0188
  -8.750  -0.1129   0.06046   0.05735  -0.1402   0.8455   0.0188
  -8.500  -0.1240   0.05702   0.05388  -0.1404   0.8433   0.0188
  -8.250  -0.1366   0.05443   0.05125  -0.1389   0.8409   0.0188
  -8.000  -0.1420   0.05154   0.04823  -0.1378   0.8385   0.0189
  -7.750  -0.1444   0.04870   0.04524  -0.1365   0.8363   0.0190
  -7.500  -0.1443   0.04587   0.04221  -0.1351   0.8343   0.0190
  -7.250  -0.1579   0.03969   0.03581  -0.1333   0.8323   0.0197
  -7.000  -0.1471   0.03766   0.03373  -0.1327   0.8308   0.0202
  -6.750  -0.1351   0.03578   0.03176  -0.1318   0.8292   0.0207
  -6.500  -0.1215   0.03396   0.02983  -0.1309   0.8275   0.0215
  -6.250  -0.1064   0.03200   0.02770  -0.1299   0.8255   0.0227
  -6.000  -0.0874   0.03029   0.02571  -0.1286   0.8236   0.0251
  -5.750  -0.0631   0.03064   0.02573  -0.1274   0.8218   0.0264
  -5.500  -0.0547   0.02513   0.01994  -0.1264   0.8201   0.0288
  -5.250  -0.0323   0.02381   0.01851  -0.1261   0.8188   0.0304
  -5.000  -0.0077   0.01954   0.01340  -0.1236   0.8175   0.0195
  -4.750   0.0167   0.01812   0.01181  -0.1231   0.8161   0.0197
  -4.500   0.0422   0.01765   0.01126  -0.1227   0.8144   0.0192
  -4.250   0.0662   0.01592   0.00945  -0.1220   0.8125   0.0184
  -4.000   0.0907   0.01496   0.00841  -0.1215   0.8106   0.0185
  -3.750   0.1155   0.01429   0.00768  -0.1210   0.8088   0.0188
  -3.500   0.1389   0.01339   0.00671  -0.1204   0.8072   0.0200
  -3.250   0.1643   0.01288   0.00619  -0.1202   0.8057   0.0222
  -3.000   0.1911   0.01263   0.00589  -0.1203   0.8045   0.0255
  -2.750   0.2177   0.01230   0.00553  -0.1203   0.8032   0.0329
  -2.500   0.2419   0.01175   0.00524  -0.1200   0.8013   0.1036
  -2.250   0.2626   0.01025   0.00505  -0.1204   0.7989   0.4751
  -2.000   0.2833   0.00974   0.00550  -0.1191   0.7967   0.7570
  -1.750   0.3106   0.01006   0.00574  -0.1189   0.7949   0.7924
  -1.500   0.3340   0.01044   0.00614  -0.1174   0.7932   0.8120
  -1.250   0.3579   0.01072   0.00640  -0.1162   0.7918   0.8257
  -1.000   0.3796   0.01101   0.00668  -0.1142   0.7903   0.8399
  -0.750   0.4004   0.01129   0.00694  -0.1122   0.7890   0.8528
  -0.500   0.4221   0.01152   0.00718  -0.1108   0.7866   0.8630
  -0.250   0.4399   0.01163   0.00732  -0.1085   0.7840   0.8689
   0.000   0.4652   0.01172   0.00738  -0.1081   0.7818   0.8746
   0.250   0.4916   0.01171   0.00735  -0.1080   0.7799   0.8783
   0.500   0.5173   0.01168   0.00730  -0.1076   0.7782   0.8809
   0.750   0.5451   0.01167   0.00727  -0.1078   0.7768   0.8833
   1.000   0.5744   0.01167   0.00724  -0.1083   0.7756   0.8853
   1.250   0.6046   0.01170   0.00724  -0.1092   0.7743   0.8870
   1.500   0.6288   0.01177   0.00735  -0.1090   0.7704   0.8888
   1.750   0.6578   0.01174   0.00733  -0.1096   0.7674   0.8902
   2.000   0.6873   0.01166   0.00725  -0.1103   0.7652   0.8912
   2.250   0.7164   0.01155   0.00715  -0.1108   0.7634   0.8922
   2.500   0.7467   0.01144   0.00704  -0.1115   0.7618   0.8931
   2.750   0.7774   0.01136   0.00696  -0.1123   0.7600   0.8939
   3.000   0.7996   0.01137   0.00704  -0.1115   0.7551   0.8953
   3.250   0.8290   0.01119   0.00689  -0.1120   0.7516   0.8962
   3.500   0.8608   0.01094   0.00665  -0.1129   0.7488   0.8971
   3.750   0.8927   0.01070   0.00641  -0.1139   0.7456   0.8979
   4.000   0.9176   0.01056   0.00635  -0.1135   0.7394   0.8988
   4.250   0.9497   0.01020   0.00599  -0.1144   0.7345   0.8994
   4.500   0.9757   0.00998   0.00585  -0.1142   0.7271   0.9004
   4.750   1.0062   0.00961   0.00547  -0.1147   0.7192   0.9013
   5.000   1.0305   0.00938   0.00530  -0.1141   0.7066   0.9022
   5.250   1.0547   0.00923   0.00516  -0.1135   0.6900   0.9030
   5.500   1.0792   0.00919   0.00516  -0.1131   0.6735   0.9037
   5.750   1.1023   0.00924   0.00516  -0.1123   0.6512   0.9044
   6.000   1.1191   0.00941   0.00524  -0.1102   0.6159   0.9057
   6.250   1.1246   0.00986   0.00546  -0.1060   0.5573   0.9073
   6.500   1.1138   0.01067   0.00594  -0.0987   0.4950   0.9095
   6.750   1.1025   0.01174   0.00672  -0.0919   0.4368   0.9119
   7.000   1.0923   0.01304   0.00774  -0.0859   0.3770   0.9144
   7.250   1.0851   0.01450   0.00890  -0.0810   0.3161   0.9168
   7.500   1.0802   0.01603   0.01010  -0.0767   0.2533   0.9193
   7.750   1.0784   0.01749   0.01124  -0.0729   0.1946   0.9214
   8.000   1.0794   0.01892   0.01238  -0.0698   0.1394   0.9234
   8.250   1.0831   0.02029   0.01349  -0.0671   0.0924   0.9255
   8.500   1.0886   0.02165   0.01463  -0.0646   0.0572   0.9276
   8.750   1.0988   0.02277   0.01568  -0.0628   0.0432   0.9295
   9.000   1.1114   0.02376   0.01671  -0.0614   0.0365   0.9315
   9.250   1.1241   0.02470   0.01769  -0.0599   0.0324   0.9337
   9.500   1.1300   0.02610   0.01916  -0.0575   0.0290   0.9366
   9.750   1.1451   0.02686   0.02000  -0.0564   0.0275   0.9398
  10.000   1.1587   0.02773   0.02094  -0.0551   0.0253   0.9442
  10.250   1.1702   0.02875   0.02202  -0.0536   0.0233   0.9503
  10.750   1.1886   0.03146   0.02494  -0.0507   0.0199   1.0000
  11.000   1.2030   0.03262   0.02617  -0.0500   0.0185   1.0000
  11.250   1.2163   0.03387   0.02748  -0.0492   0.0172   1.0000
  11.500   1.2266   0.03541   0.02906  -0.0482   0.0158   1.0000
  11.750   1.2304   0.03768   0.03145  -0.0464   0.0145   1.0000
  12.000   1.2460   0.03877   0.03262  -0.0460   0.0136   1.0000
  12.250   1.2599   0.04003   0.03395  -0.0455   0.0124   1.0000
  12.500   1.2720   0.04149   0.03547  -0.0449   0.0115   1.0000
  12.750   1.2810   0.04330   0.03735  -0.0440   0.0108   1.0000
  13.000   1.2851   0.04608   0.04028  -0.0423   0.0101   1.0000
  13.250   1.2964   0.04775   0.04209  -0.0417   0.0097   1.0000
  13.500   1.3064   0.04964   0.04413  -0.0410   0.0093   1.0000
  13.750   1.3149   0.05174   0.04638  -0.0402   0.0089   1.0000
  14.000   1.3222   0.05406   0.04885  -0.0394   0.0086   1.0000
  14.250   1.3276   0.05650   0.05144  -0.0387   0.0083   1.0000
  14.500   1.3315   0.05918   0.05428  -0.0381   0.0080   1.0000
  14.750   1.3336   0.06210   0.05736  -0.0376   0.0079   1.0000
  15.000   1.3339   0.06523   0.06065  -0.0372   0.0077   1.0000
  15.250   1.3320   0.06878   0.06437  -0.0369   0.0076   1.0000
  15.500   1.3285   0.07256   0.06831  -0.0368   0.0074   1.0000
  15.750   1.3222   0.07686   0.07278  -0.0370   0.0073   1.0000
  16.000   1.3127   0.08173   0.07787  -0.0374   0.0072   1.0000
  16.250   1.2999   0.08733   0.08368  -0.0383   0.0071   1.0000
  16.500   1.2856   0.09334   0.08991  -0.0398   0.0071   1.0000
  16.750   1.2681   0.10015   0.09694  -0.0420   0.0071   1.0000
  17.000   1.2513   0.10716   0.10416  -0.0448   0.0071   1.0000
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