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FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)
Reynolds number: 100,000
Max Cl/Cd: 58.14 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74modsm-il-100000-n5.txt
Download as CSV file: xf-fx74modsm-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000   0.2177   0.10185   0.09606  -0.1192   0.7572   0.0296
  -8.750   0.2291   0.09958   0.09371  -0.1208   0.7470   0.0305
  -8.500   0.2389   0.09763   0.09173  -0.1223   0.7367   0.0313
  -8.250   0.2479   0.09610   0.09016  -0.1242   0.7278   0.0318
  -8.000   0.2551   0.09492   0.08894  -0.1262   0.7189   0.0321
  -7.750   0.2617   0.09373   0.08774  -0.1281   0.7107   0.0323
  -7.500   0.2687   0.09234   0.08633  -0.1300   0.7029   0.0324
  -7.250   0.2825   0.08839   0.08234  -0.1297   0.6961   0.0327
  -7.000   0.2974   0.08467   0.07857  -0.1290   0.6891   0.0335
  -6.750   0.3090   0.08230   0.07613  -0.1294   0.6831   0.0343
  -6.500   0.3185   0.08029   0.07413  -0.1298   0.6760   0.0352
  -6.250   0.3280   0.07838   0.07218  -0.1305   0.6702   0.0362
  -6.000   0.3359   0.07671   0.07051  -0.1310   0.6643   0.0372
  -5.750   0.3463   0.07501   0.06881  -0.1326   0.6583   0.0388
  -5.500   0.3634   0.07405   0.06780  -0.1391   0.6534   0.0406
  -5.250   0.3907   0.07258   0.06633  -0.1495   0.6474   0.0412
  -5.000   0.3894   0.06879   0.06256  -0.1417   0.6424   0.0424
  -4.750   0.4028   0.06646   0.06017  -0.1413   0.6379   0.0441
  -4.500   0.4189   0.06438   0.05808  -0.1433   0.6327   0.0458
  -4.250   0.4388   0.06219   0.05588  -0.1468   0.6275   0.0481
  -4.000   0.4992   0.05927   0.05276  -0.1664   0.6227   0.0521
  -3.750   0.5245   0.05575   0.04920  -0.1709   0.6184   0.0530
  -3.500   0.5302   0.05367   0.04718  -0.1672   0.6135   0.0544
  -3.250   0.5508   0.05154   0.04499  -0.1684   0.6090   0.0568
  -3.000   0.6082   0.04815   0.04133  -0.1815   0.6050   0.0643
  -2.750   0.6414   0.04511   0.03828  -0.1870   0.5999   0.0691
  -2.500   0.6996   0.04184   0.03474  -0.1988   0.5951   0.0830
  -2.250   0.7259   0.03993   0.03277  -0.2002   0.5913   0.0874
  -2.000   0.7787   0.03719   0.02977  -0.2090   0.5870   0.1018
  -1.500   0.9242   0.02901   0.02011  -0.2309   0.5778   0.0435
  -1.250   0.9720   0.02759   0.01796  -0.2351   0.5744   0.0416
  -1.000   1.0076   0.02671   0.01677  -0.2371   0.5700   0.0414
  -0.750   1.0418   0.02583   0.01565  -0.2388   0.5655   0.0417
  -0.500   1.0744   0.02518   0.01486  -0.2403   0.5616   0.0447
  -0.250   1.1070   0.02475   0.01418  -0.2413   0.5584   0.0474
   0.000   1.1352   0.02447   0.01383  -0.2415   0.5542   0.0486
   0.250   1.1634   0.02428   0.01357  -0.2418   0.5501   0.0504
   0.500   1.1934   0.02408   0.01330  -0.2424   0.5464   0.0544
   0.750   1.2252   0.02398   0.01308  -0.2434   0.5433   0.0612
   1.000   1.2541   0.02406   0.01307  -0.2439   0.5394   0.0682
   1.250   1.2826   0.02416   0.01317  -0.2444   0.5352   0.0885
   1.500   1.3136   0.02337   0.01380  -0.2455   0.5318   0.7109
   1.750   1.3270   0.02312   0.01366  -0.2422   0.5289   1.0000
   2.000   1.3553   0.02346   0.01376  -0.2425   0.5259   1.0000
   2.250   1.3784   0.02396   0.01420  -0.2420   0.5215   1.0000
   2.500   1.4035   0.02439   0.01451  -0.2418   0.5178   1.0000
   2.750   1.4301   0.02476   0.01474  -0.2418   0.5147   1.0000
   3.000   1.4581   0.02508   0.01490  -0.2421   0.5121   1.0000
   3.250   1.4807   0.02560   0.01539  -0.2415   0.5084   1.0000
   3.500   1.5023   0.02615   0.01594  -0.2407   0.5044   1.0000
   3.750   1.5262   0.02659   0.01634  -0.2403   0.5010   1.0000
   4.000   1.5521   0.02696   0.01661  -0.2402   0.4982   1.0000
   4.250   1.5798   0.02729   0.01683  -0.2405   0.4959   1.0000
   4.500   1.5964   0.02804   0.01768  -0.2390   0.4919   1.0000
   4.750   1.6159   0.02865   0.01835  -0.2379   0.4881   1.0000
   5.000   1.6384   0.02912   0.01880  -0.2373   0.4849   1.0000
   5.250   1.6636   0.02949   0.01912  -0.2371   0.4822   1.0000
   5.500   1.6886   0.02993   0.01950  -0.2369   0.4798   1.0000
   5.750   1.7001   0.03088   0.02065  -0.2347   0.4758   1.0000
   6.000   1.7163   0.03161   0.02145  -0.2331   0.4722   1.0000
   6.250   1.7369   0.03213   0.02199  -0.2323   0.4692   1.0000
   6.500   1.7616   0.03250   0.02232  -0.2320   0.4666   1.0000
   6.750   1.7819   0.03310   0.02299  -0.2312   0.4640   1.0000
   7.000   1.7854   0.03436   0.02445  -0.2278   0.4600   1.0000
   7.250   1.7959   0.03529   0.02548  -0.2254   0.4565   1.0000
   7.500   1.8127   0.03589   0.02613  -0.2240   0.4536   1.0000
   7.750   1.8373   0.03624   0.02647  -0.2237   0.4512   1.0000
   8.000   1.8471   0.03719   0.02755  -0.2213   0.4483   1.0000
   8.250   1.8322   0.03922   0.02981  -0.2155   0.4441   1.0000
   8.500   1.8335   0.04064   0.03135  -0.2122   0.4406   1.0000
   8.750   1.8489   0.04136   0.03214  -0.2108   0.4378   1.0000
   9.000   1.8756   0.04155   0.03234  -0.2108   0.4356   1.0000
   9.250   1.8462   0.04491   0.03595  -0.2043   0.4310   1.0000
   9.500   1.8135   0.04911   0.04038  -0.1986   0.4259   1.0000
   9.750   1.8229   0.05041   0.04178  -0.1970   0.4229   1.0000
  10.000   1.8510   0.05026   0.04168  -0.1970   0.4209   1.0000
  10.500   1.7399   0.06575   0.05759  -0.1873   0.4063   1.0000
  10.750   1.7723   0.06474   0.05664  -0.1870   0.4052   1.0000
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