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HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il)
Reynolds number: 50,000
Max Cl/Cd: 36.43 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1712-il-50000.txt
Download as CSV file: xf-hs1712-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-712 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3791   0.11978   0.11316  -0.0202   1.0000   0.2001
  -7.750  -0.4092   0.12014   0.11368  -0.0182   1.0000   0.2029
  -7.500  -0.4428   0.12079   0.11451  -0.0201   1.0000   0.2042
  -7.250  -0.3971   0.11249   0.10612  -0.0146   1.0000   0.2132
  -7.000  -0.4125   0.11111   0.10485  -0.0129   1.0000   0.2193
  -6.750  -0.4425   0.11123   0.10512  -0.0181   1.0000   0.2232
  -6.500  -0.4206   0.10540   0.09931  -0.0108   1.0000   0.2297
  -6.250  -0.4257   0.10320   0.09718  -0.0107   1.0000   0.2386
  -6.000  -0.4335   0.10032   0.09438  -0.0131   1.0000   0.2446
  -5.750  -0.4257   0.09706   0.09115  -0.0092   1.0000   0.2517
  -5.500  -0.4300   0.09440   0.08854  -0.0143   1.0000   0.2631
  -5.250  -0.4232   0.09113   0.08533  -0.0096   1.0000   0.2698
  -5.000  -0.4200   0.08808   0.08230  -0.0126   1.0000   0.2835
  -4.750  -0.4132   0.08532   0.07955  -0.0143   1.0000   0.3010
  -4.500  -0.4061   0.08252   0.07678  -0.0138   1.0000   0.3195
  -4.250  -0.3994   0.07969   0.07399  -0.0120   1.0000   0.3385
  -4.000  -0.3925   0.07697   0.07132  -0.0097   1.0000   0.3583
  -3.750  -0.3848   0.07443   0.06882  -0.0075   1.0000   0.3804
  -3.500  -0.2235   0.05692   0.04919  -0.0617   1.0000   0.1854
  -3.250  -0.1992   0.05353   0.04577  -0.0630   1.0000   0.1802
  -3.000  -0.1629   0.05026   0.04206  -0.0671   1.0000   0.1784
  -2.750  -0.1260   0.04754   0.03881  -0.0708   1.0000   0.1790
  -2.500  -0.0876   0.04556   0.03606  -0.0742   1.0000   0.1847
  -2.250  -0.0630   0.04442   0.03497  -0.0750   1.0000   0.1937
  -2.000  -0.0298   0.04350   0.03346  -0.0770   1.0000   0.2045
  -1.750  -0.0043   0.04272   0.03269  -0.0777   1.0000   0.2158
  -1.500   0.0243   0.04214   0.03186  -0.0787   1.0000   0.2306
  -1.250   0.0537   0.04169   0.03123  -0.0798   1.0000   0.2504
  -1.000   0.0828   0.04140   0.03082  -0.0808   1.0000   0.2826
  -0.750   0.1109   0.04128   0.03074  -0.0815   1.0000   0.3250
  -0.500   0.1391   0.04139   0.03103  -0.0824   1.0000   0.3813
  -0.250   0.1694   0.04153   0.03156  -0.0837   1.0000   0.4606
   0.000   0.1922   0.04039   0.03224  -0.0814   1.0000   0.7976
   0.250   0.1953   0.04070   0.03214  -0.0788   1.0000   1.0000
   0.500   0.2167   0.04190   0.03291  -0.0792   1.0000   1.0000
   0.750   0.2750   0.04343   0.03396  -0.0862   0.9843   1.0000
   1.000   0.3230   0.04451   0.03474  -0.0913   0.9664   1.0000
   1.250   0.3655   0.04550   0.03551  -0.0952   0.9504   1.0000
   1.500   0.4074   0.04640   0.03623  -0.0988   0.9344   1.0000
   1.750   0.4495   0.04715   0.03684  -0.1023   0.9177   1.0000
   2.000   0.4915   0.04775   0.03733  -0.1055   0.9007   1.0000
   2.250   0.5336   0.04823   0.03771  -0.1085   0.8837   1.0000
   2.500   0.5758   0.04856   0.03797  -0.1114   0.8667   1.0000
   2.750   0.6188   0.04870   0.03807  -0.1141   0.8495   1.0000
   3.000   0.6632   0.04861   0.03795  -0.1168   0.8324   1.0000
   3.250   0.6939   0.04877   0.03811  -0.1173   0.8120   1.0000
   3.500   0.7346   0.04846   0.03783  -0.1189   0.7931   1.0000
   3.750   0.7839   0.04764   0.03703  -0.1214   0.7771   1.0000
   4.000   0.8123   0.04759   0.03700  -0.1210   0.7555   1.0000
   4.250   0.8589   0.04644   0.03592  -0.1225   0.7393   1.0000
   4.500   0.9037   0.04520   0.03472  -0.1236   0.7232   1.0000
   4.750   0.9490   0.04376   0.03333  -0.1245   0.7074   1.0000
   5.000   0.9977   0.04218   0.03183  -0.1259   0.6919   1.0000
   5.250   1.0552   0.04022   0.02994  -0.1286   0.6762   1.0000
   5.500   1.1146   0.03852   0.02831  -0.1319   0.6589   1.0000
   5.750   1.1623   0.03762   0.02744  -0.1339   0.6395   1.0000
   6.000   1.2031   0.03724   0.02710  -0.1350   0.6196   1.0000
   6.250   1.2391   0.03719   0.02708  -0.1355   0.5999   1.0000
   6.500   1.2734   0.03729   0.02718  -0.1358   0.5807   1.0000
   6.750   1.3082   0.03739   0.02729  -0.1362   0.5618   1.0000
   7.000   1.3386   0.03768   0.02756  -0.1360   0.5427   1.0000
   7.250   1.3699   0.03791   0.02775  -0.1358   0.5238   1.0000
   7.500   1.3969   0.03834   0.02816  -0.1351   0.5050   1.0000
   7.750   1.4195   0.03900   0.02882  -0.1337   0.4863   1.0000
   8.000   1.4422   0.03970   0.02951  -0.1324   0.4678   1.0000
   8.250   1.4651   0.04051   0.03034  -0.1312   0.4497   1.0000
   8.500   1.4810   0.04166   0.03157  -0.1290   0.4326   1.0000
   8.750   1.4972   0.04283   0.03281  -0.1269   0.4154   1.0000
   9.000   1.5129   0.04405   0.03411  -0.1248   0.3984   1.0000
   9.250   1.5292   0.04527   0.03538  -0.1227   0.3813   1.0000
   9.500   1.5468   0.04657   0.03671  -0.1209   0.3643   1.0000
   9.750   1.5645   0.04809   0.03826  -0.1192   0.3476   1.0000
  10.000   1.5760   0.05010   0.04040  -0.1168   0.3325   1.0000
  10.250   1.5843   0.05228   0.04274  -0.1139   0.3183   1.0000
  10.500   1.5946   0.05440   0.04496  -0.1113   0.3047   1.0000
  10.750   1.6135   0.05618   0.04677  -0.1099   0.2909   1.0000
  11.000   1.5909   0.05929   0.05031  -0.1030   0.2832   1.0000
  11.250   1.6064   0.06123   0.05228  -0.1013   0.2721   1.0000
  11.500   1.5748   0.06482   0.05624  -0.0937   0.2674   1.0000
  11.750   1.6061   0.06631   0.05768  -0.0942   0.2561   1.0000
  12.000   1.5614   0.07067   0.06240  -0.0858   0.2545   1.0000
  12.250   1.5096   0.07645   0.06848  -0.0786   0.2537   1.0000
  12.500   1.4430   0.08478   0.07707  -0.0732   0.2544   1.0000
  12.750   1.3524   0.09841   0.09084  -0.0719   0.2564   1.0000
  13.000   1.0529   0.16050   0.15238  -0.1042   0.2864   1.0000
  13.250   1.0564   0.16660   0.15855  -0.1063   0.2899   1.0000
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