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

UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il)
Reynolds number: 200,000
Max Cl/Cd: 37.17 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ua79sf18-il-200000.txt
Download as CSV file: xf-ua79sf18-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.0176   0.11260   0.10847  -0.1533   0.8705   0.0415
 -12.750  -0.0235   0.10876   0.10468  -0.1565   0.8702   0.0421
 -12.500  -0.0261   0.10478   0.10073  -0.1590   0.8700   0.0422
 -12.250  -0.0304   0.10029   0.09628  -0.1619   0.8698   0.0423
 -12.000  -0.0204   0.09702   0.09304  -0.1596   0.8697   0.0442
 -11.750  -0.0139   0.09476   0.09079  -0.1598   0.8692   0.0454
 -11.500  -0.0113   0.09209   0.08814  -0.1605   0.8686   0.0467
 -11.250  -0.0132   0.08881   0.08490  -0.1619   0.8682   0.0481
 -11.000  -0.0196   0.08489   0.08101  -0.1637   0.8671   0.0495
 -10.750  -0.0336   0.07952   0.07569  -0.1669   0.8659   0.0500
 -10.500  -0.0570   0.07438   0.07054  -0.1699   0.8652   0.0506
 -10.250  -0.0798   0.07101   0.06716  -0.1707   0.8648   0.0503
 -10.000  -0.1054   0.06861   0.06473  -0.1698   0.8643   0.0500
  -9.750  -0.1336   0.06697   0.06305  -0.1672   0.8633   0.0501
  -9.500  -0.1632   0.06618   0.06223  -0.1630   0.8623   0.0502
  -9.250  -0.2009   0.06739   0.06348  -0.1553   0.8620   0.0493
  -8.500  -0.4857   0.09397   0.09091  -0.0834   0.9087   0.0411
  -8.250  -0.5104   0.09134   0.08816  -0.0814   0.9041   0.0410
  -8.000  -0.5376   0.08918   0.08591  -0.0765   0.8947   0.0411
  -7.750  -0.5538   0.08771   0.08403  -0.0746   0.8898   0.0420
  -7.500  -0.5748   0.08597   0.08211  -0.0690   0.8809   0.0421
  -7.250  -0.5833   0.08100   0.07681  -0.0677   0.8770   0.0426
  -7.000  -0.5765   0.07403   0.06990  -0.0688   0.8759   0.0442
  -6.750  -0.5584   0.07146   0.06730  -0.0699   0.8748   0.0458
  -6.500  -0.5769   0.06926   0.06503  -0.0634   0.8651   0.0463
  -6.250  -0.5619   0.06674   0.06231  -0.0634   0.8630   0.0495
  -4.750  -0.4783   0.05023   0.04347  -0.0506   0.8402   0.0290
  -4.500  -0.4518   0.04675   0.03961  -0.0501   0.8383   0.0245
  -4.250  -0.4191   0.04500   0.03735  -0.0496   0.8369   0.0212
  -4.000  -0.3862   0.04453   0.03666  -0.0503   0.8358   0.0208
  -3.750  -0.3886   0.04308   0.03515  -0.0456   0.8286   0.0212
  -3.500  -0.3626   0.04217   0.03422  -0.0455   0.8255   0.0223
  -3.250  -0.3319   0.04204   0.03408  -0.0465   0.8236   0.0254
  -3.000  -0.2994   0.04189   0.03388  -0.0475   0.8224   0.0270
  -2.750  -0.3033   0.04105   0.03302  -0.0429   0.8137   0.0274
  -2.500  -0.2732   0.04071   0.03259  -0.0435   0.8110   0.0294
  -2.250  -0.2395   0.04053   0.03230  -0.0449   0.8095   0.0342
  -2.000  -0.2383   0.04009   0.03181  -0.0413   0.8014   0.0396
  -1.750  -0.2260   0.03791   0.03230  -0.0391   0.7982   0.6744
  -1.500  -0.2007   0.03956   0.03423  -0.0359   0.7960   0.7339
  -1.250  -0.2075   0.03984   0.03465  -0.0287   0.7861   0.7614
  -1.000  -0.1875   0.04114   0.03602  -0.0241   0.7831   0.7915
  -0.750  -0.1802   0.04112   0.03596  -0.0199   0.7722   0.8048
  -0.500  -0.1387   0.04058   0.03525  -0.0209   0.7585   0.8103
  -0.250  -0.1068   0.04043   0.03491  -0.0220   0.7500   0.8139
   0.000  -0.0749   0.04043   0.03477  -0.0234   0.7452   0.8161
   0.250  -0.0357   0.04049   0.03470  -0.0255   0.7430   0.8175
   0.500   0.0065   0.04070   0.03478  -0.0281   0.7418   0.8185
   0.750   0.0083   0.04062   0.03467  -0.0252   0.7315   0.8202
   1.000   0.0481   0.04068   0.03461  -0.0275   0.7297   0.8211
   1.250   0.0567   0.04088   0.03478  -0.0258   0.7208   0.8221
   1.500   0.0911   0.04095   0.03476  -0.0275   0.7184   0.8230
   1.750   0.1295   0.04098   0.03471  -0.0297   0.7169   0.8239
   2.000   0.1381   0.04129   0.03499  -0.0280   0.7076   0.8250
   2.250   0.1729   0.04131   0.03494  -0.0298   0.7053   0.8256
   2.500   0.2106   0.04130   0.03487  -0.0319   0.7038   0.8265
   2.750   0.2506   0.04122   0.03474  -0.0342   0.7028   0.8274
   3.000   0.2563   0.04154   0.03505  -0.0322   0.6921   0.8288
   3.250   0.2952   0.04130   0.03478  -0.0342   0.6905   0.8298
   3.500   0.3351   0.04097   0.03443  -0.0363   0.6895   0.8305
   3.750   0.3406   0.04142   0.03489  -0.0342   0.6790   0.8313
   4.000   0.3775   0.04116   0.03462  -0.0359   0.6775   0.8318
   4.250   0.4156   0.04081   0.03428  -0.0377   0.6765   0.8326
   4.500   0.4225   0.04133   0.03483  -0.0358   0.6662   0.8338
   4.750   0.4605   0.04086   0.03437  -0.0375   0.6647   0.8344
   5.000   0.5003   0.04025   0.03379  -0.0395   0.6636   0.8351
   5.250   0.5099   0.04071   0.03428  -0.0379   0.6532   0.8361
   5.500   0.5478   0.04009   0.03370  -0.0395   0.6516   0.8369
   5.750   0.5863   0.03947   0.03313  -0.0413   0.6506   0.8379
   6.000   0.5949   0.04011   0.03382  -0.0396   0.6399   0.8392
   6.250   0.6321   0.03948   0.03325  -0.0412   0.6384   0.8403
   6.500   0.6702   0.03876   0.03258  -0.0428   0.6372   0.8416
   6.750   0.6809   0.03937   0.03327  -0.0414   0.6266   0.8432
   7.000   0.7171   0.03858   0.03258  -0.0426   0.6249   0.8447
   7.250   0.7544   0.03769   0.03180  -0.0439   0.6236   0.8465
   7.500   0.7988   0.03573   0.02995  -0.0454   0.6215   0.8484
   8.250   0.9254   0.02743   0.02158  -0.0469   0.5503   0.8557
   8.500   0.9644   0.02614   0.02004  -0.0478   0.5030   0.8582
   8.750   0.9797   0.02636   0.01998  -0.0461   0.4527   0.8612
   9.000   0.9829   0.02748   0.02089  -0.0433   0.4102   0.8653
   9.250   0.9646   0.02994   0.02281  -0.0384   0.3338   0.8705
   9.500   0.9566   0.03205   0.02459  -0.0349   0.2771   0.8758
   9.750   0.9499   0.03427   0.02645  -0.0319   0.2160   0.8826
  10.000   0.9372   0.03702   0.02865  -0.0286   0.1316   0.8906
  10.250   0.9263   0.03985   0.03096  -0.0257   0.0503   0.9016
  10.500   0.9282   0.04199   0.03293  -0.0241   0.0163   0.9179
  10.750   0.9489   0.04326   0.03439  -0.0253   0.0143   0.9502
  11.000   0.9610   0.04447   0.03573  -0.0247   0.0134   1.0000
  11.250   0.9755   0.04588   0.03724  -0.0246   0.0133   1.0000
  11.500   0.9876   0.04744   0.03894  -0.0242   0.0132   1.0000
  11.750   0.9978   0.04915   0.04079  -0.0236   0.0129   1.0000
  12.000   1.0068   0.05097   0.04277  -0.0229   0.0129   1.0000
  12.250   1.0138   0.05300   0.04494  -0.0221   0.0129   1.0000
  12.500   1.0183   0.05529   0.04737  -0.0213   0.0130   1.0000
  12.750   1.0219   0.05770   0.04990  -0.0204   0.0130   1.0000
  13.000   1.0235   0.06035   0.05266  -0.0196   0.0131   1.0000
  13.250   1.0249   0.06306   0.05547  -0.0187   0.0132   1.0000
  13.500   1.0274   0.06566   0.05814  -0.0179   0.0132   1.0000
  13.750   1.0320   0.06802   0.06057  -0.0172   0.0134   1.0000
  14.000   1.0410   0.06994   0.06255  -0.0166   0.0136   1.0000
  14.250   1.0529   0.07158   0.06424  -0.0161   0.0138   1.0000
  14.500   1.0664   0.07308   0.06581  -0.0157   0.0141   1.0000
  14.750   1.0808   0.07450   0.06732  -0.0153   0.0146   1.0000
  15.000   1.1024   0.07524   0.06821  -0.0145   0.0155   1.0000
  15.250   1.1343   0.07539   0.06861  -0.0135   0.0171   1.0000
  15.500   1.2126   0.07512   0.06852  -0.0136   0.0207   1.0000
  15.750   1.2097   0.07718   0.07078  -0.0126   0.0216   1.0000
  16.000   0.9946   0.08349   0.07829  -0.0073   0.0185   1.0000
  16.250   1.0314   0.08330   0.07826  -0.0062   0.0207   1.0000
  16.500   1.0227   0.08615   0.08132  -0.0066   0.0214   1.0000
  16.750   1.0030   0.09093   0.08658  -0.0070   0.0234   1.0000
  17.000   0.9797   0.09630   0.09233  -0.0083   0.0247   1.0000
  17.250   0.9583   0.10158   0.09790  -0.0100   0.0257   1.0000
  17.500   0.9367   0.10703   0.10358  -0.0123   0.0263   1.0000
  17.750   0.9134   0.11291   0.10969  -0.0152   0.0268   1.0000
  18.000   0.8895   0.11919   0.11616  -0.0187   0.0269   1.0000
  18.250   0.8638   0.12609   0.12326  -0.0229   0.0270   1.0000
  18.500   0.8385   0.13339   0.13075  -0.0278   0.0266   1.0000
  18.750   0.8093   0.14205   0.13958  -0.0336   0.0262   1.0000
<< Back to UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il)

Polar data table (+)

Polar graphs


<< Back to UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il)