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FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)
Reynolds number: 500,000
Max Cl/Cd: 118.67 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74modsm-il-500000.txt
Download as CSV file: xf-fx74modsm-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-Cl5-140 MOD  (smoothed)                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.1617   0.11475   0.11146  -0.1184   0.7872   0.0103
 -11.000   0.1698   0.11255   0.10914  -0.1189   0.7668   0.0104
 -10.750   0.1783   0.11035   0.10684  -0.1195   0.7495   0.0105
 -10.500   0.1871   0.10811   0.10451  -0.1203   0.7344   0.0106
 -10.250   0.1961   0.10586   0.10219  -0.1211   0.7210   0.0108
 -10.000   0.2053   0.10361   0.09987  -0.1219   0.7092   0.0110
  -9.750   0.2145   0.10136   0.09755  -0.1228   0.6987   0.0112
  -9.500   0.2241   0.09907   0.09522  -0.1237   0.6888   0.0114
  -9.250   0.2338   0.09681   0.09291  -0.1247   0.6801   0.0117
  -9.000   0.2435   0.09454   0.09059  -0.1256   0.6716   0.0120
  -8.750   0.2535   0.09227   0.08829  -0.1267   0.6641   0.0123
  -8.500   0.2638   0.09007   0.08605  -0.1280   0.6567   0.0126
  -8.250   0.2733   0.08802   0.08397  -0.1296   0.6503   0.0127
  -8.000   0.2823   0.08601   0.08196  -0.1314   0.6440   0.0128
  -7.750   0.2903   0.08406   0.07998  -0.1332   0.6383   0.0128
  -7.250   0.3123   0.07848   0.07437  -0.1340   0.6271   0.0131
  -7.000   0.3231   0.07634   0.07218  -0.1343   0.6218   0.0133
  -6.750   0.3341   0.07430   0.07014  -0.1351   0.6166   0.0136
  -6.500   0.3446   0.07230   0.06814  -0.1359   0.6114   0.0139
  -6.250   0.3545   0.07037   0.06617  -0.1366   0.6068   0.0143
  -6.000   0.3636   0.06853   0.06434  -0.1373   0.6025   0.0148
  -5.750   0.3761   0.06650   0.06232  -0.1390   0.5981   0.0157
  -5.500   0.3948   0.06431   0.06012  -0.1443   0.5938   0.0162
  -5.250   0.4164   0.06173   0.05749  -0.1501   0.5898   0.0163
  -5.000   0.4399   0.05887   0.05464  -0.1553   0.5857   0.0163
  -4.750   0.4567   0.05584   0.05161  -0.1576   0.5815   0.0165
  -4.500   0.4695   0.05385   0.04959  -0.1571   0.5773   0.0167
  -4.250   0.4889   0.05179   0.04747  -0.1592   0.5734   0.0171
  -4.000   0.5135   0.04940   0.04510  -0.1632   0.5696   0.0176
  -3.750   0.5433   0.04670   0.04237  -0.1687   0.5656   0.0184
  -3.500   0.6286   0.04015   0.03562  -0.1923   0.5614   0.0205
  -3.250   0.6566   0.03695   0.03234  -0.1965   0.5576   0.0211
  -3.000   0.6854   0.03508   0.03046  -0.1995   0.5537   0.0218
  -2.500   0.8180   0.02611   0.02090  -0.2247   0.5458   0.0266
  -2.250   0.8546   0.02463   0.01928  -0.2284   0.5419   0.0279
  -2.000   0.9063   0.02336   0.01757  -0.2335   0.5382   0.0323
  -1.500   0.9870   0.01933   0.01323  -0.2419   0.5305   0.0381
  -1.250   1.0302   0.01805   0.01151  -0.2455   0.5269   0.0430
  -1.000   1.0635   0.01720   0.01061  -0.2473   0.5237   0.0459
  -0.750   1.0911   0.01781   0.01105  -0.2467   0.5200   0.0522
  -0.500   1.1308   0.01587   0.00897  -0.2503   0.5164   0.0593
  -0.250   1.1688   0.01471   0.00739  -0.2515   0.5131   0.0381
   0.000   1.2026   0.01403   0.00650  -0.2526   0.5100   0.0338
   0.250   1.2333   0.01368   0.00614  -0.2533   0.5068   0.0342
   0.500   1.2634   0.01348   0.00593  -0.2539   0.5034   0.0356
   0.750   1.2924   0.01342   0.00583  -0.2544   0.5001   0.0384
   1.000   1.3213   0.01346   0.00579  -0.2547   0.4968   0.0409
   1.250   1.3520   0.01334   0.00565  -0.2555   0.4937   0.0469
   1.500   1.3811   0.01331   0.00562  -0.2560   0.4906   0.0649
   1.750   1.4167   0.01260   0.00617  -0.2584   0.4874   0.7157
   2.000   1.4393   0.01258   0.00633  -0.2573   0.4844   0.8459
   2.250   1.4614   0.01258   0.00635  -0.2562   0.4814   1.0000
   2.500   1.4883   0.01276   0.00649  -0.2562   0.4784   1.0000
   2.750   1.5149   0.01290   0.00661  -0.2561   0.4753   1.0000
   3.000   1.5413   0.01307   0.00674  -0.2561   0.4724   1.0000
   3.250   1.5674   0.01326   0.00688  -0.2559   0.4695   1.0000
   3.500   1.5933   0.01351   0.00705  -0.2558   0.4665   1.0000
   3.750   1.6191   0.01374   0.00725  -0.2557   0.4636   1.0000
   4.000   1.6444   0.01389   0.00742  -0.2554   0.4606   1.0000
   4.250   1.6696   0.01408   0.00761  -0.2551   0.4577   1.0000
   4.500   1.6946   0.01428   0.00779  -0.2548   0.4549   1.0000
   4.750   1.7193   0.01454   0.00800  -0.2545   0.4520   1.0000
   5.000   1.7443   0.01483   0.00825  -0.2542   0.4491   1.0000
   5.250   1.7681   0.01501   0.00849  -0.2537   0.4463   1.0000
   5.500   1.7919   0.01521   0.00872  -0.2532   0.4434   1.0000
   5.750   1.8155   0.01543   0.00895  -0.2527   0.4406   1.0000
   6.000   1.8388   0.01570   0.00919  -0.2521   0.4378   1.0000
   6.250   1.8629   0.01607   0.00952  -0.2518   0.4347   1.0000
   6.500   1.8847   0.01627   0.00980  -0.2509   0.4322   1.0000
   6.750   1.9066   0.01650   0.01009  -0.2501   0.4293   1.0000
   7.000   1.9283   0.01676   0.01039  -0.2493   0.4265   1.0000
   7.250   1.9494   0.01704   0.01069  -0.2483   0.4239   1.0000
   7.500   1.9704   0.01739   0.01102  -0.2474   0.4210   1.0000
   7.750   1.9902   0.01773   0.01140  -0.2463   0.4182   1.0000
   8.000   2.0081   0.01800   0.01178  -0.2447   0.4155   1.0000
   8.250   2.0261   0.01832   0.01215  -0.2432   0.4127   1.0000
   8.500   2.0438   0.01865   0.01253  -0.2417   0.4100   1.0000
   8.750   2.0621   0.01904   0.01293  -0.2403   0.4072   1.0000
   9.000   2.0816   0.01950   0.01340  -0.2393   0.4042   1.0000
   9.250   2.0951   0.01987   0.01391  -0.2370   0.4011   1.0000
   9.500   2.1057   0.02028   0.01440  -0.2343   0.3959   1.0000
   9.750   2.1159   0.02089   0.01495  -0.2317   0.3896   1.0000
  10.000   2.1258   0.02140   0.01562  -0.2290   0.3840   1.0000
  10.250   2.1369   0.02203   0.01630  -0.2267   0.3790   1.0000
  10.500   2.1462   0.02281   0.01711  -0.2242   0.3736   1.0000
  10.750   2.1574   0.02351   0.01793  -0.2221   0.3676   1.0000
  11.000   2.1650   0.02447   0.01891  -0.2195   0.3620   1.0000
  11.250   2.1741   0.02541   0.01996  -0.2174   0.3554   1.0000
  11.500   2.1771   0.02678   0.02134  -0.2145   0.3468   1.0000
  11.750   2.1814   0.02817   0.02281  -0.2120   0.3365   1.0000
  12.000   2.1806   0.03006   0.02472  -0.2092   0.3246   1.0000
  12.250   2.1731   0.03266   0.02731  -0.2060   0.3086   1.0000
  12.500   2.1566   0.03626   0.03086  -0.2024   0.2897   1.0000
  12.750   2.1357   0.04061   0.03516  -0.1991   0.2688   1.0000
  13.000   2.1093   0.04580   0.04030  -0.1958   0.2484   1.0000
  13.250   2.0797   0.05159   0.04606  -0.1929   0.2300   1.0000
  13.500   2.0508   0.05756   0.05202  -0.1903   0.2129   1.0000
  13.750   2.0188   0.06409   0.05854  -0.1881   0.1963   1.0000
  14.000   1.9882   0.07065   0.06510  -0.1861   0.1814   1.0000
  14.250   1.9569   0.07749   0.07194  -0.1845   0.1665   1.0000
  14.500   1.9261   0.08439   0.07884  -0.1831   0.1522   1.0000
  14.750   1.8972   0.09121   0.08565  -0.1821   0.1379   1.0000
  15.000   1.8672   0.09832   0.09275  -0.1814   0.1219   1.0000
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