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CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: CLARK K AIRFOIL (clarkk-il)
Reynolds number: 200,000
Max Cl/Cd: 71.52 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkk-il-200000-n5.txt
Download as CSV file: xf-clarkk-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK K 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4269   0.08925   0.08536  -0.0448   1.0000   0.0420
  -9.750  -0.4372   0.08400   0.08015  -0.0473   1.0000   0.0428
  -9.500  -0.4575   0.07776   0.07399  -0.0501   1.0000   0.0434
  -9.250  -0.4970   0.07083   0.06718  -0.0522   1.0000   0.0437
  -9.000  -0.5716   0.04720   0.04254  -0.0735   0.9851   0.0454
  -8.750  -0.5448   0.04600   0.04142  -0.0747   0.9814   0.0460
  -8.500  -0.5215   0.04383   0.03913  -0.0768   0.9766   0.0468
  -8.250  -0.4984   0.04108   0.03615  -0.0792   0.9723   0.0478
  -8.000  -0.4777   0.03831   0.03307  -0.0808   0.9661   0.0492
  -7.750  -0.4533   0.03529   0.02956  -0.0830   0.9621   0.0505
  -7.500  -0.4331   0.03304   0.02688  -0.0833   0.9547   0.0514
  -7.250  -0.4051   0.03185   0.02510  -0.0844   0.9505   0.0526
  -7.000  -0.3836   0.02935   0.02247  -0.0846   0.9434   0.0533
  -6.750  -0.3551   0.02773   0.02071  -0.0855   0.9391   0.0539
  -6.500  -0.3284   0.02640   0.01925  -0.0859   0.9333   0.0544
  -6.250  -0.3015   0.02521   0.01792  -0.0862   0.9271   0.0549
  -6.000  -0.2712   0.02414   0.01669  -0.0871   0.9229   0.0558
  -5.750  -0.2469   0.02325   0.01566  -0.0867   0.9146   0.0567
  -5.500  -0.2177   0.02227   0.01451  -0.0871   0.9092   0.0572
  -5.250  -0.1915   0.02142   0.01349  -0.0869   0.9016   0.0576
  -5.000  -0.1636   0.02061   0.01253  -0.0869   0.8949   0.0580
  -4.750  -0.1356   0.01987   0.01166  -0.0869   0.8883   0.0584
  -4.500  -0.1089   0.01922   0.01088  -0.0867   0.8804   0.0588
  -4.000  -0.0538   0.01816   0.00960  -0.0864   0.8658   0.0601
  -3.750  -0.0252   0.01770   0.00903  -0.0864   0.8592   0.0607
  -3.500   0.0014   0.01725   0.00852  -0.0861   0.8508   0.0610
  -3.250   0.0293   0.01679   0.00798  -0.0859   0.8435   0.0612
  -3.000   0.0563   0.01635   0.00752  -0.0857   0.8353   0.0615
  -2.750   0.0833   0.01570   0.00688  -0.0854   0.8276   0.0619
  -2.500   0.1098   0.01518   0.00637  -0.0852   0.8196   0.0624
  -2.250   0.1365   0.01473   0.00594  -0.0849   0.8112   0.0629
  -2.000   0.1630   0.01435   0.00558  -0.0845   0.8030   0.0635
  -1.750   0.1897   0.01403   0.00526  -0.0842   0.7945   0.0641
  -1.500   0.2162   0.01375   0.00500  -0.0839   0.7858   0.0649
  -1.250   0.2430   0.01350   0.00474  -0.0836   0.7772   0.0662
  -1.000   0.2696   0.01330   0.00454  -0.0833   0.7679   0.0676
  -0.750   0.2968   0.01313   0.00432  -0.0830   0.7592   0.0686
  -0.500   0.3233   0.01299   0.00416  -0.0827   0.7492   0.0693
  -0.250   0.3505   0.01287   0.00399  -0.0824   0.7401   0.0700
   0.000   0.3773   0.01277   0.00387  -0.0821   0.7296   0.0708
   0.250   0.4041   0.01270   0.00375  -0.0818   0.7191   0.0716
   0.500   0.4311   0.01261   0.00361  -0.0814   0.7087   0.0731
   0.750   0.4575   0.01254   0.00351  -0.0810   0.6963   0.0749
   1.000   0.4838   0.01249   0.00343  -0.0805   0.6822   0.0772
   1.250   0.5100   0.01246   0.00336  -0.0801   0.6671   0.0804
   1.500   0.5361   0.01242   0.00332  -0.0796   0.6525   0.0892
   1.750   0.5612   0.01211   0.00336  -0.0792   0.6395   0.2132
   2.000   0.5862   0.01187   0.00342  -0.0787   0.6266   0.3104
   2.250   0.6002   0.01054   0.00366  -0.0757   0.6142   0.7949
   2.500   0.6589   0.01043   0.00376  -0.0817   0.5972   0.9993
   2.750   0.6835   0.01058   0.00382  -0.0810   0.5829   1.0000
   3.000   0.7077   0.01074   0.00391  -0.0802   0.5686   1.0000
   3.250   0.7318   0.01092   0.00400  -0.0794   0.5535   1.0000
   3.500   0.7557   0.01111   0.00411  -0.0785   0.5380   1.0000
   3.750   0.7797   0.01132   0.00425  -0.0777   0.5228   1.0000
   4.000   0.8035   0.01153   0.00440  -0.0769   0.5073   1.0000
   4.250   0.8271   0.01177   0.00457  -0.0760   0.4904   1.0000
   4.500   0.8506   0.01202   0.00476  -0.0752   0.4731   1.0000
   4.750   0.8740   0.01228   0.00497  -0.0743   0.4560   1.0000
   5.000   0.8971   0.01256   0.00519  -0.0734   0.4383   1.0000
   5.250   0.9198   0.01286   0.00544  -0.0725   0.4193   1.0000
   5.500   0.9421   0.01319   0.00570  -0.0715   0.4000   1.0000
   5.750   0.9642   0.01355   0.00600  -0.0705   0.3815   1.0000
   6.000   0.9861   0.01392   0.00632  -0.0694   0.3640   1.0000
   6.250   1.0077   0.01431   0.00666  -0.0684   0.3461   1.0000
   6.500   1.0287   0.01474   0.00703  -0.0673   0.3262   1.0000
   6.750   1.0490   0.01520   0.00743  -0.0661   0.3067   1.0000
   7.000   1.0690   0.01569   0.00784  -0.0648   0.2880   1.0000
   7.250   1.0884   0.01621   0.00829  -0.0635   0.2698   1.0000
   7.500   1.1072   0.01675   0.00876  -0.0622   0.2514   1.0000
   7.750   1.1260   0.01729   0.00924  -0.0608   0.2346   1.0000
   8.000   1.1450   0.01782   0.00974  -0.0595   0.2194   1.0000
   8.250   1.1629   0.01840   0.01028  -0.0581   0.2026   1.0000
   8.500   1.1806   0.01897   0.01083  -0.0567   0.1850   1.0000
   8.750   1.1970   0.01958   0.01140  -0.0550   0.1648   1.0000
   9.000   1.2102   0.02034   0.01205  -0.0529   0.1404   1.0000
   9.250   1.2184   0.02146   0.01295  -0.0503   0.1028   1.0000
   9.750   1.2274   0.02441   0.01549  -0.0446   0.0457   1.0000
  10.000   1.2360   0.02564   0.01670  -0.0424   0.0384   1.0000
  10.250   1.2463   0.02676   0.01789  -0.0405   0.0347   1.0000
  10.500   1.2552   0.02801   0.01921  -0.0386   0.0319   1.0000
  10.750   1.2610   0.02952   0.02078  -0.0365   0.0297   1.0000
  11.000   1.2699   0.03082   0.02220  -0.0349   0.0283   1.0000
  11.250   1.2772   0.03230   0.02380  -0.0332   0.0271   1.0000
  11.500   1.2829   0.03394   0.02555  -0.0317   0.0260   1.0000
  11.750   1.2871   0.03578   0.02749  -0.0302   0.0249   1.0000
  12.000   1.2883   0.03794   0.02975  -0.0288   0.0241   1.0000
  12.250   1.2855   0.04058   0.03248  -0.0275   0.0233   1.0000
  12.500   1.2893   0.04269   0.03471  -0.0266   0.0226   1.0000
  12.750   1.2916   0.04501   0.03716  -0.0258   0.0219   1.0000
  13.000   1.2926   0.04755   0.03982  -0.0251   0.0214   1.0000
  13.250   1.2924   0.05027   0.04265  -0.0245   0.0209   1.0000
  13.500   1.2918   0.05311   0.04560  -0.0241   0.0204   1.0000
  13.750   1.2907   0.05609   0.04868  -0.0239   0.0199   1.0000
  14.000   1.2891   0.05921   0.05189  -0.0239   0.0195   1.0000
  14.250   1.2869   0.06249   0.05526  -0.0239   0.0191   1.0000
  14.500   1.2837   0.06596   0.05880  -0.0241   0.0187   1.0000
  14.750   1.2799   0.06948   0.06238  -0.0242   0.0184   1.0000
  15.000   1.2799   0.07274   0.06579  -0.0246   0.0180   1.0000
  15.250   1.2791   0.07615   0.06933  -0.0251   0.0176   1.0000
  15.500   1.2779   0.07966   0.07298  -0.0257   0.0172   1.0000
  15.750   1.2763   0.08327   0.07670  -0.0263   0.0169   1.0000
  16.000   1.2745   0.08692   0.08048  -0.0270   0.0166   1.0000
  16.250   1.2725   0.09067   0.08434  -0.0279   0.0163   1.0000
  16.500   1.2704   0.09449   0.08828  -0.0288   0.0161   1.0000
  16.750   1.2681   0.09838   0.09228  -0.0299   0.0158   1.0000
  17.000   1.2656   0.10234   0.09634  -0.0311   0.0156   1.0000
  17.250   1.2630   0.10636   0.10045  -0.0324   0.0154   1.0000
  17.500   1.2607   0.11038   0.10457  -0.0339   0.0152   1.0000
  17.750   1.2584   0.11440   0.10866  -0.0354   0.0150   1.0000
  18.000   1.2567   0.11829   0.11261  -0.0368   0.0147   1.0000
  18.250   1.2524   0.12282   0.11726  -0.0387   0.0146   1.0000
  18.500   1.2449   0.12828   0.12290  -0.0415   0.0144   1.0000
  18.750   1.2366   0.13406   0.12888  -0.0446   0.0142   1.0000
  19.000   1.2275   0.14016   0.13516  -0.0481   0.0141   1.0000
  19.250   1.2175   0.14664   0.14183  -0.0519   0.0139   1.0000
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