Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 78-PK-188/20 (fx78pk188-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 78-PK-188/20 (fx78pk188-il)
Reynolds number: 200,000
Max Cl/Cd: 38.14 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx78pk188-il-200000.txt
Download as CSV file: xf-fx78pk188-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-PK-188/20                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.1729   0.11063   0.10681  -0.0959   0.8434   0.0778
 -13.250  -0.3827   0.07576   0.07153  -0.1251   0.8538   0.0440
 -13.000  -0.4089   0.07018   0.06584  -0.1266   0.8520   0.0431
 -12.750  -0.4365   0.06514   0.06067  -0.1272   0.8502   0.0419
 -12.500  -0.5384   0.05578   0.05064  -0.1234   0.8477   0.0370
 -12.250  -0.5586   0.05383   0.04843  -0.1204   0.8453   0.0364
 -12.000  -0.5725   0.05158   0.04597  -0.1176   0.8431   0.0363
 -11.750  -0.5820   0.04978   0.04396  -0.1147   0.8410   0.0361
 -11.500  -0.5946   0.04679   0.04071  -0.1113   0.8391   0.0363
 -11.250  -0.6023   0.04413   0.03777  -0.1080   0.8374   0.0364
 -11.000  -0.6023   0.04109   0.03447  -0.1057   0.8356   0.0368
 -10.750  -0.5914   0.03913   0.03246  -0.1049   0.8336   0.0383
 -10.500  -0.5791   0.03802   0.03130  -0.1037   0.8317   0.0398
 -10.250  -0.5719   0.03715   0.03030  -0.1015   0.8298   0.0416
 -10.000  -0.5632   0.03590   0.02880  -0.0993   0.8280   0.0432
  -9.750  -0.5495   0.03455   0.02715  -0.0977   0.8265   0.0444
  -9.500  -0.5399   0.03407   0.02640  -0.0953   0.8249   0.0455
  -9.250  -0.4903   0.03075   0.02304  -0.1001   0.8243   0.0498
  -9.000  -0.4656   0.02990   0.02208  -0.1001   0.8230   0.0524
  -8.750  -0.4405   0.02916   0.02118  -0.0999   0.8218   0.0549
  -8.500  -0.4154   0.02862   0.02049  -0.1000   0.8202   0.0564
  -8.250  -0.3669   0.02712   0.01907  -0.1034   0.8195   0.0603
  -8.000  -0.3440   0.02671   0.01868  -0.1033   0.8180   0.0631
  -7.750  -0.3224   0.02634   0.01828  -0.1028   0.8164   0.0657
  -7.500  -0.3036   0.02605   0.01794  -0.1019   0.8148   0.0680
  -7.250  -0.2904   0.02552   0.01744  -0.1003   0.8130   0.0712
  -7.000  -0.2797   0.02514   0.01709  -0.0983   0.8111   0.0754
  -6.750  -0.2681   0.02486   0.01677  -0.0962   0.8094   0.0805
  -6.500  -0.2634   0.02447   0.01641  -0.0931   0.8080   0.0865
  -6.250  -0.2578   0.02427   0.01620  -0.0900   0.8068   0.0962
  -6.000  -0.2794   0.02517   0.01720  -0.0832   0.8030   0.1013
  -5.750  -0.3039   0.02612   0.01818  -0.0752   0.7990   0.1057
  -5.500  -0.3229   0.02663   0.01876  -0.0680   0.7965   0.1180
  -5.250  -0.3373   0.02631   0.01876  -0.0615   0.7943   0.1687
  -5.000  -0.3498   0.02510   0.01826  -0.0554   0.7925   0.3014
  -4.750  -0.3840   0.02664   0.01967  -0.0457   0.7898   0.2802
  -4.500  -0.4200   0.02807   0.02091  -0.0357   0.7867   0.2522
  -4.250  -0.4383   0.02759   0.02105  -0.0292   0.7865   0.3734
  -4.000  -0.4553   0.02693   0.02146  -0.0220   0.7853   0.5579
  -3.750  -0.4513   0.02803   0.02295  -0.0174   0.7856   0.6606
  -3.500  -0.4418   0.02901   0.02387  -0.0146   0.7863   0.6910
  -3.250  -0.4314   0.02999   0.02477  -0.0119   0.7867   0.7109
  -3.000  -0.4124   0.03117   0.02587  -0.0105   0.7890   0.7258
  -2.750  -0.4606   0.03227   0.02702  -0.0014   0.8135   0.7280
  -2.500  -0.3198   0.03291   0.02745  -0.0127   0.7763   0.7614
  -2.250  -0.3317   0.03398   0.02856  -0.0065   0.7754   0.7686
  -2.000  -0.3174   0.03524   0.02981  -0.0035   0.7758   0.7812
  -1.750  -0.2999   0.03638   0.03092  -0.0011   0.7767   0.7937
  -1.500  -0.3571   0.03724   0.03187   0.0089   0.7938   0.7968
  -1.250  -0.3256   0.03884   0.03345   0.0102   0.7922   0.8121
  -1.000  -0.3435   0.03834   0.03294   0.0173   0.7830   0.8225
  -0.750  -0.2587   0.03838   0.03280   0.0123   0.7602   0.8327
  -0.500  -0.2437   0.03881   0.03316   0.0132   0.7606   0.8373
  -0.250  -0.2471   0.03916   0.03350   0.0171   0.7597   0.8407
   0.000  -0.2193   0.03866   0.03292   0.0171   0.7491   0.8436
   0.250  -0.2214   0.03923   0.03346   0.0198   0.7504   0.8478
   0.500  -0.1662   0.03836   0.03245   0.0163   0.7347   0.8494
   0.750  -0.1403   0.03829   0.03231   0.0161   0.7278   0.8518
   1.000  -0.1265   0.03839   0.03237   0.0177   0.7225   0.8541
   1.250  -0.0926   0.03842   0.03235   0.0165   0.7195   0.8560
   1.500  -0.0497   0.03842   0.03229   0.0140   0.7176   0.8575
   1.750  -0.0558   0.03869   0.03255   0.0178   0.7080   0.8612
   2.000  -0.0239   0.03876   0.03258   0.0165   0.7052   0.8633
   2.250   0.0164   0.03875   0.03251   0.0142   0.7033   0.8651
   2.500   0.0590   0.03877   0.03250   0.0116   0.7021   0.8663
   2.750   0.0461   0.03908   0.03283   0.0166   0.6910   0.8693
   3.000   0.0827   0.03904   0.03277   0.0150   0.6891   0.8708
   3.250   0.1232   0.03898   0.03270   0.0129   0.6879   0.8719
   3.500   0.1179   0.03944   0.03317   0.0164   0.6768   0.8749
   3.750   0.1545   0.03935   0.03308   0.0148   0.6749   0.8766
   4.000   0.1948   0.03920   0.03292   0.0127   0.6736   0.8779
   4.250   0.1962   0.03966   0.03338   0.0152   0.6625   0.8802
   4.500   0.2336   0.03943   0.03316   0.0135   0.6607   0.8816
   4.750   0.2717   0.03913   0.03289   0.0120   0.6594   0.8829
   5.000   0.2707   0.03975   0.03354   0.0150   0.6484   0.8855
   5.250   0.3063   0.03951   0.03333   0.0136   0.6466   0.8869
   5.500   0.3445   0.03917   0.03303   0.0120   0.6453   0.8882
   5.750   0.3457   0.03994   0.03383   0.0144   0.6344   0.8908
   6.000   0.3819   0.03958   0.03352   0.0131   0.6325   0.8926
   6.250   0.4195   0.03920   0.03319   0.0115   0.6313   0.8945
   6.500   0.4230   0.03990   0.03393   0.0137   0.6203   0.8970
   6.750   0.4584   0.03945   0.03355   0.0126   0.6185   0.8986
   7.000   0.4956   0.03890   0.03309   0.0113   0.6171   0.9003
   7.250   0.5019   0.03951   0.03376   0.0132   0.6061   0.9031
   7.500   0.5436   0.03843   0.03275   0.0117   0.6043   0.9050
   7.750   0.5813   0.03717   0.03158   0.0109   0.5996   0.9073
   8.000   0.6117   0.03615   0.03064   0.0109   0.5920   0.9101
   8.250   0.6569   0.03441   0.02901   0.0094   0.5901   0.9122
   8.500   0.7063   0.03223   0.02696   0.0076   0.5888   0.9143
   8.750   0.7202   0.03224   0.02707   0.0090   0.5774   0.9179
   9.000   0.7625   0.03056   0.02551   0.0078   0.5752   0.9207
   9.250   0.7796   0.03050   0.02554   0.0088   0.5640   0.9246
   9.500   0.8222   0.02877   0.02395   0.0075   0.5575   0.9276
   9.750   0.8451   0.02847   0.02375   0.0078   0.5411   0.9320
  10.000   0.8769   0.02762   0.02297   0.0074   0.5205   0.9367
  10.250   0.9287   0.02546   0.02073   0.0055   0.4857   0.9404
  10.500   0.9569   0.02509   0.02008   0.0054   0.4283   0.9458
  10.750   0.9610   0.02664   0.02126   0.0066   0.3663   0.9539
  11.000   0.9601   0.02919   0.02347   0.0071   0.3038   0.9638
  11.250   0.9535   0.03200   0.02591   0.0081   0.2387   1.0000
  11.500   0.9426   0.03466   0.02819   0.0104   0.1901   1.0000
  11.750   0.9390   0.03700   0.03027   0.0120   0.1578   1.0000
  12.000   0.9415   0.03899   0.03212   0.0130   0.1342   1.0000
  12.250   0.9462   0.04088   0.03386   0.0138   0.1180   1.0000
  12.500   0.9534   0.04262   0.03552   0.0143   0.1046   1.0000
  12.750   0.9626   0.04426   0.03714   0.0147   0.0939   1.0000
  13.000   0.9711   0.04594   0.03881   0.0151   0.0857   1.0000
  13.250   0.9773   0.04782   0.04061   0.0157   0.0776   1.0000
  13.500   0.9889   0.04934   0.04222   0.0159   0.0698   1.0000
  13.750   0.9954   0.05124   0.04409   0.0164   0.0631   1.0000
  14.000   1.0036   0.05310   0.04600   0.0166   0.0552   1.0000
  14.250   1.0102   0.05511   0.04804   0.0171   0.0477   1.0000
  14.500   1.0138   0.05742   0.05031   0.0177   0.0411   1.0000
  14.750   1.0209   0.05946   0.05239   0.0178   0.0364   1.0000
  15.000   1.0257   0.06165   0.05457   0.0185   0.0331   1.0000
  15.250   1.0340   0.06360   0.05661   0.0188   0.0303   1.0000
  15.500   1.0408   0.06568   0.05871   0.0191   0.0283   1.0000
  15.750   1.0513   0.06731   0.06030   0.0199   0.0266   1.0000
  16.000   1.0588   0.06948   0.06265   0.0200   0.0250   1.0000
  16.250   1.0658   0.07167   0.06497   0.0200   0.0237   1.0000
  16.500   1.0738   0.07375   0.06714   0.0201   0.0229   1.0000
  16.750   1.0808   0.07595   0.06937   0.0200   0.0219   1.0000
  17.000   1.0908   0.07789   0.07135   0.0203   0.0212   1.0000
  17.250   1.0975   0.08052   0.07416   0.0207   0.0205   1.0000
  17.500   1.0993   0.08360   0.07745   0.0206   0.0202   1.0000
  17.750   1.0969   0.08725   0.08133   0.0203   0.0199   1.0000
  18.000   1.0920   0.09131   0.08564   0.0197   0.0196   1.0000
  18.250   1.0862   0.09557   0.09012   0.0189   0.0195   1.0000
  18.500   1.0757   0.10056   0.09535   0.0177   0.0193   1.0000
  18.750   1.0624   0.10611   0.10115   0.0160   0.0193   1.0000
  19.000   1.0483   0.11194   0.10721   0.0138   0.0193   1.0000
  19.250   1.0297   0.11876   0.11427   0.0110   0.0193   1.0000
<< Back to FX 78-PK-188/20 (fx78pk188-il)

Polar data table (+)

Polar graphs


<< Back to FX 78-PK-188/20 (fx78pk188-il)