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Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 52.28 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cp-180-050-gn-1000000.txt
Download as CSV file: xf-cp-180-050-gn-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=18% T=5% R=0.78                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000   0.5214   0.11449   0.11181  -0.2813   0.9074   0.0119
 -14.750   0.5224   0.11305   0.11038  -0.2798   0.9042   0.0120
 -14.500   0.5293   0.11117   0.10849  -0.2803   0.9016   0.0120
 -14.250   0.5401   0.10863   0.10592  -0.2823   0.8995   0.0121
 -14.000   0.5563   0.10625   0.10350  -0.2856   0.8977   0.0121
 -13.750   0.5769   0.10384   0.10106  -0.2901   0.8959   0.0123
 -13.500   0.5836   0.10250   0.09971  -0.2901   0.8934   0.0126
 -13.250   0.5821   0.10163   0.09886  -0.2874   0.8901   0.0130
 -13.000   0.5875   0.10021   0.09743  -0.2870   0.8872   0.0132
 -12.750   0.5991   0.09824   0.09544  -0.2886   0.8849   0.0140
 -12.500   0.6154   0.09589   0.09305  -0.2917   0.8828   0.0143
 -12.250   0.6362   0.09313   0.09024  -0.2964   0.8807   0.0144
 -12.000   0.6320   0.09237   0.08951  -0.2929   0.8776   0.0144
 -11.750   0.6498   0.07421   0.07144  -0.2802   0.8610   0.0146
 -11.500   0.6532   0.07298   0.07022  -0.2790   0.8580   0.0148
 -11.250   0.6608   0.07158   0.06881  -0.2790   0.8555   0.0152
 -11.000   0.6719   0.06975   0.06695  -0.2802   0.8530   0.0156
 -10.750   0.6883   0.06752   0.06467  -0.2831   0.8506   0.0162
 -10.500   0.6821   0.06690   0.06409  -0.2790   0.8476   0.0164
 -10.250   0.6784   0.06593   0.06313  -0.2757   0.8441   0.0168
 -10.000   0.6774   0.06470   0.06190  -0.2734   0.8408   0.0170
  -9.750   0.6863   0.06297   0.06014  -0.2740   0.8382   0.0171
  -8.750   0.6963   0.07485   0.07191  -0.2832   0.8388   0.0173
  -8.500   0.7136   0.07319   0.07020  -0.2856   0.8361   0.0175
  -8.250   0.7081   0.07271   0.06975  -0.2815   0.8330   0.0176
  -8.000   0.7019   0.07227   0.06934  -0.2771   0.8294   0.0179
  -7.750   0.7003   0.07152   0.06859  -0.2742   0.8259   0.0180
  -7.500   0.7072   0.07033   0.06738  -0.2736   0.8229   0.0185
  -7.250   0.7237   0.06866   0.06566  -0.2759   0.8200   0.0192
  -7.000   0.6979   0.06919   0.06627  -0.2661   0.8160   0.0190
  -6.750   0.6857   0.06888   0.06600  -0.2603   0.8120   0.0195
  -6.500   0.6817   0.06820   0.06530  -0.2569   0.8084   0.0197
  -6.250   0.6893   0.06691   0.06397  -0.2571   0.8049   0.0199
  -6.000   0.6638   0.06736   0.06450  -0.2478   0.8009   0.0199
  -5.750   0.6509   0.06708   0.06425  -0.2421   0.7967   0.0199
  -5.500   0.6513   0.06606   0.06322  -0.2402   0.7931   0.0199
  -5.250   0.6643   0.06399   0.06111  -0.2412   0.7902   0.0200
  -5.000   0.6620   0.06317   0.06032  -0.2381   0.7871   0.0201
  -4.750   0.6485   0.06295   0.06015  -0.2321   0.7831   0.0202
  -4.500   0.6482   0.06220   0.05940  -0.2294   0.7796   0.0203
  -4.250   0.6583   0.06095   0.05813  -0.2294   0.7766   0.0206
  -4.000   0.6799   0.05918   0.05631  -0.2324   0.7738   0.0209
  -3.750   0.6699   0.05885   0.05604  -0.2273   0.7703   0.0212
  -3.500   0.6685   0.05811   0.05532  -0.2245   0.7667   0.0216
  -3.250   0.6760   0.05690   0.05411  -0.2239   0.7635   0.0222
  -3.000   0.6942   0.05514   0.05231  -0.2260   0.7606   0.0226
  -2.750   0.7313   0.05276   0.04986  -0.2332   0.7579   0.0228
  -2.250   0.7372   0.05055   0.04771  -0.2295   0.7514   0.0229
  -2.000   0.7482   0.04936   0.04652  -0.2292   0.7484   0.0231
  -1.750   0.7699   0.04794   0.04507  -0.2314   0.7457   0.0234
  -1.500   0.8007   0.04623   0.04331  -0.2357   0.7433   0.0239
  -1.250   0.8364   0.04438   0.04142  -0.2412   0.7410   0.0249
  -1.000   0.8519   0.04332   0.04038  -0.2420   0.7381   0.0256
  -0.750   0.8935   0.04166   0.03869  -0.2491   0.7356   0.0258
  -0.500   0.9340   0.03989   0.03689  -0.2557   0.7332   0.0259
  -0.250   0.9541   0.03839   0.03537  -0.2569   0.7306   0.0261
   0.000   0.9885   0.03703   0.03398  -0.2613   0.7284   0.0264
   0.250   1.0339   0.03546   0.03234  -0.2681   0.7263   0.0270
   0.500   1.0778   0.03401   0.03087  -0.2746   0.7243   0.0283
   0.750   1.1376   0.03269   0.02949  -0.2848   0.7221   0.0289
   1.000   1.1874   0.03125   0.02802  -0.2925   0.7196   0.0290
   1.250   1.1984   0.03050   0.02724  -0.2911   0.7126   0.0291
   1.500   1.2375   0.02942   0.02609  -0.2957   0.7087   0.0295
   1.750   1.2600   0.02909   0.02579  -0.2968   0.7050   0.0299
   2.000   1.2969   0.02834   0.02502  -0.3009   0.7017   0.0310
   2.250   1.3482   0.02765   0.02422  -0.3079   0.6955   0.0319
   2.500   1.4037   0.02685   0.02333  -0.3158   0.6914   0.0320
   6.500   1.3567   0.05898   0.05236  -0.2558   0.0215   0.0358
   6.750   1.3750   0.05995   0.05333  -0.2558   0.0200   0.0362
   7.000   1.3953   0.06098   0.05434  -0.2560   0.0193   0.0369
   7.250   1.4178   0.06210   0.05545  -0.2566   0.0188   0.0384
   7.500   1.4506   0.06343   0.05667  -0.2586   0.0185   0.0394
   7.750   1.4702   0.06449   0.05772  -0.2589   0.0182   0.0399
   8.000   1.4853   0.06579   0.05902  -0.2582   0.0180   0.0403
   8.250   1.5019   0.06712   0.06036  -0.2577   0.0179   0.0409
   8.500   1.5192   0.06859   0.06181  -0.2573   0.0177   0.0420
   8.750   1.5487   0.06998   0.06306  -0.2588   0.0176   0.0445
   9.000   1.5600   0.07164   0.06475  -0.2575   0.0174   0.0451
   9.250   1.5725   0.07329   0.06641  -0.2564   0.0172   0.0461
   9.500   1.5931   0.07494   0.06791  -0.2561   0.0171   0.0493
   9.750   1.6056   0.07681   0.06981  -0.2554   0.0169   0.0505
  10.000   1.6147   0.07879   0.07183  -0.2539   0.0167   0.0514
  10.250   1.6257   0.08074   0.07377  -0.2526   0.0165   0.0534
  10.500   1.6374   0.08290   0.07584  -0.2516   0.0163   0.0568
  10.750   1.6446   0.08520   0.07819  -0.2500   0.0162   0.0580
  11.000   1.6522   0.08748   0.08050  -0.2485   0.0160   0.0604
  11.250   1.6586   0.09005   0.08306  -0.2470   0.0158   0.0651
  11.500   1.6638   0.09266   0.08572  -0.2454   0.0157   0.0673
  11.750   1.6679   0.09522   0.08830  -0.2435   0.0155   0.0715
  12.000   1.6785   0.09795   0.09088  -0.2427   0.0153   0.0483
  12.250   1.6806   0.10103   0.09399  -0.2410   0.0151   0.0480
  12.500   1.6827   0.10410   0.09711  -0.2394   0.0149   0.0475
  12.750   1.6851   0.10711   0.10018  -0.2378   0.0149   0.0472
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