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

GEMINI (smoothed) (geminism-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GEMINI (smoothed) (geminism-il)
Reynolds number: 100,000
Max Cl/Cd: 48.65 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-geminism-il-100000-n5.txt
Download as CSV file: xf-geminism-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GEMINI (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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5948   0.08648   0.08093  -0.0588   1.0000   0.0363
 -12.750  -0.6286   0.07693   0.07125  -0.0653   1.0000   0.0360
 -12.500  -0.6589   0.06951   0.06369  -0.0700   1.0000   0.0359
 -12.250  -0.6862   0.06372   0.05772  -0.0726   1.0000   0.0358
 -12.000  -0.7112   0.05913   0.05294  -0.0734   1.0000   0.0358
 -11.750  -0.7344   0.05548   0.04908  -0.0724   1.0000   0.0358
 -11.500  -0.7563   0.05257   0.04597  -0.0696   1.0000   0.0360
 -11.250  -0.7776   0.05029   0.04349  -0.0652   1.0000   0.0361
 -11.000  -0.7962   0.04819   0.04115  -0.0602   1.0000   0.0363
 -10.750  -0.8053   0.04611   0.03892  -0.0563   1.0000   0.0367
 -10.500  -0.8065   0.04455   0.03732  -0.0530   1.0000   0.0373
 -10.250  -0.8072   0.04329   0.03601  -0.0496   1.0000   0.0380
 -10.000  -0.8085   0.04209   0.03472  -0.0460   1.0000   0.0388
  -9.750  -0.8100   0.04086   0.03336  -0.0421   1.0000   0.0398
  -9.500  -0.8108   0.03956   0.03189  -0.0383   1.0000   0.0407
  -9.250  -0.8048   0.03795   0.03003  -0.0358   0.9988   0.0419
  -9.000  -0.7783   0.03567   0.02732  -0.0370   0.9929   0.0434
  -8.750  -0.7497   0.03372   0.02512  -0.0384   0.9871   0.0451
  -8.500  -0.7202   0.03239   0.02376  -0.0399   0.9812   0.0473
  -8.250  -0.6897   0.03104   0.02225  -0.0413   0.9754   0.0497
  -8.000  -0.6582   0.02963   0.02060  -0.0427   0.9697   0.0520
  -7.750  -0.6292   0.02833   0.01917  -0.0436   0.9627   0.0545
  -7.500  -0.5974   0.02720   0.01806  -0.0453   0.9572   0.0579
  -7.250  -0.5693   0.02622   0.01698  -0.0459   0.9494   0.0613
  -7.000  -0.5357   0.02517   0.01579  -0.0475   0.9443   0.0650
  -6.750  -0.5094   0.02420   0.01485  -0.0479   0.9363   0.0696
  -6.500  -0.4769   0.02334   0.01388  -0.0492   0.9305   0.0756
  -6.250  -0.4528   0.02246   0.01301  -0.0490   0.9215   0.0814
  -6.000  -0.4223   0.02166   0.01214  -0.0500   0.9151   0.0913
  -5.750  -0.3991   0.02093   0.01142  -0.0494   0.9053   0.1035
  -5.500  -0.3703   0.02002   0.01068  -0.0501   0.8989   0.1269
  -5.250  -0.3495   0.01929   0.01017  -0.0491   0.8885   0.1702
  -5.000  -0.3211   0.01854   0.00964  -0.0496   0.8821   0.2300
  -4.750  -0.3000   0.01804   0.00929  -0.0486   0.8717   0.2769
  -4.500  -0.2742   0.01749   0.00891  -0.0483   0.8641   0.3283
  -4.250  -0.2515   0.01705   0.00865  -0.0474   0.8547   0.3797
  -4.000  -0.2275   0.01668   0.00843  -0.0466   0.8463   0.4334
  -3.750  -0.2038   0.01635   0.00828  -0.0456   0.8376   0.4903
  -3.500  -0.1816   0.01614   0.00821  -0.0442   0.8286   0.5468
  -3.250  -0.1558   0.01595   0.00810  -0.0433   0.8206   0.5920
  -3.000  -0.1313   0.01585   0.00801  -0.0423   0.8113   0.6214
  -2.750  -0.1022   0.01571   0.00781  -0.0422   0.8036   0.6469
  -2.500  -0.0772   0.01565   0.00773  -0.0414   0.7939   0.6699
  -2.250  -0.0475   0.01554   0.00755  -0.0414   0.7866   0.6934
  -2.000  -0.0220   0.01552   0.00751  -0.0406   0.7765   0.7139
  -1.750   0.0086   0.01545   0.00738  -0.0408   0.7690   0.7350
  -1.500   0.0352   0.01544   0.00736  -0.0403   0.7591   0.7555
  -1.250   0.0651   0.01543   0.00728  -0.0403   0.7509   0.7762
  -1.000   0.0956   0.01544   0.00728  -0.0405   0.7417   0.7965
  -0.750   0.1267   0.01549   0.00729  -0.0408   0.7328   0.8182
  -0.500   0.1581   0.01553   0.00728  -0.0411   0.7241   0.8410
  -0.250   0.1920   0.01563   0.00735  -0.0420   0.7144   0.8597
   0.000   0.2278   0.01567   0.00730  -0.0433   0.7063   0.8754
   0.250   0.2601   0.01576   0.00736  -0.0441   0.6957   0.8905
   0.500   0.2981   0.01583   0.00735  -0.0460   0.6866   0.9025
   0.750   0.3352   0.01591   0.00737  -0.0479   0.6767   0.9140
   1.000   0.3706   0.01600   0.00740  -0.0494   0.6665   0.9260
   1.250   0.4068   0.01605   0.00736  -0.0511   0.6577   0.9377
   1.500   0.4475   0.01615   0.00743  -0.0539   0.6463   0.9458
   1.750   0.4854   0.01624   0.00748  -0.0561   0.6360   0.9550
   2.000   0.5232   0.01630   0.00747  -0.0583   0.6265   0.9644
   2.250   0.5630   0.01640   0.00757  -0.0611   0.6148   0.9721
   2.500   0.6012   0.01649   0.00762  -0.0635   0.6043   0.9809
   2.750   0.6393   0.01656   0.00764  -0.0659   0.5944   0.9899
   3.000   0.6777   0.01668   0.00778  -0.0686   0.5827   0.9986
   3.250   0.7008   0.01679   0.00786  -0.0681   0.5727   1.0000
   3.500   0.7201   0.01689   0.00792  -0.0667   0.5636   1.0000
   3.750   0.7381   0.01705   0.00810  -0.0651   0.5534   1.0000
   4.000   0.7575   0.01719   0.00821  -0.0636   0.5445   1.0000
   4.250   0.7760   0.01737   0.00840  -0.0621   0.5347   1.0000
   4.500   0.7949   0.01757   0.00859  -0.0605   0.5253   1.0000
   4.750   0.8147   0.01776   0.00876  -0.0591   0.5164   1.0000
   5.000   0.8331   0.01800   0.00905  -0.0575   0.5067   1.0000
   5.250   0.8534   0.01823   0.00924  -0.0562   0.4983   1.0000
   5.500   0.8718   0.01850   0.00956  -0.0546   0.4886   1.0000
   5.750   0.8915   0.01877   0.00985  -0.0531   0.4798   1.0000
   6.000   0.9108   0.01905   0.01015  -0.0516   0.4708   1.0000
   6.250   0.9298   0.01936   0.01051  -0.0501   0.4618   1.0000
   6.500   0.9499   0.01965   0.01082  -0.0488   0.4534   1.0000
   6.750   0.9680   0.02001   0.01126  -0.0471   0.4442   1.0000
   7.000   0.9885   0.02032   0.01157  -0.0458   0.4362   1.0000
   7.250   1.0049   0.02068   0.01204  -0.0439   0.4256   1.0000
   7.500   1.0207   0.02101   0.01242  -0.0418   0.4133   1.0000
   7.750   1.0350   0.02134   0.01275  -0.0394   0.3993   1.0000
   8.000   1.0477   0.02168   0.01311  -0.0367   0.3843   1.0000
   8.250   1.0601   0.02207   0.01352  -0.0341   0.3697   1.0000
   8.500   1.0722   0.02249   0.01397  -0.0315   0.3558   1.0000
   8.750   1.0828   0.02295   0.01447  -0.0287   0.3411   1.0000
   9.000   1.0912   0.02346   0.01502  -0.0256   0.3245   1.0000
   9.250   1.0974   0.02403   0.01562  -0.0222   0.3077   1.0000
   9.500   1.1014   0.02468   0.01628  -0.0185   0.2892   1.0000
   9.750   1.1025   0.02553   0.01707  -0.0147   0.2670   1.0000
  10.000   1.1033   0.02658   0.01807  -0.0113   0.2402   1.0000
<< Back to GEMINI (smoothed) (geminism-il)

Polar data table (+)

Polar graphs


<< Back to GEMINI (smoothed) (geminism-il)