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RAE 2822 AIRFOIL (rae2822-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAE 2822 AIRFOIL (rae2822-il)
Reynolds number: 100,000
Max Cl/Cd: 37.54 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae2822-il-100000-n5.txt
Download as CSV file: xf-rae2822-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 2822 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6530   0.08807   0.08258  -0.0487   1.0000   0.0263
 -12.250  -0.6780   0.08008   0.07451  -0.0536   1.0000   0.0259
 -12.000  -0.7023   0.07341   0.06773  -0.0573   1.0000   0.0257
 -11.750  -0.7253   0.06775   0.06192  -0.0598   1.0000   0.0256
 -11.500  -0.7463   0.06297   0.05698  -0.0611   1.0000   0.0255
 -11.250  -0.7654   0.05890   0.05273  -0.0615   1.0000   0.0255
 -11.000  -0.7830   0.05542   0.04907  -0.0608   1.0000   0.0255
 -10.750  -0.8005   0.05243   0.04587  -0.0589   1.0000   0.0256
 -10.500  -0.8166   0.04994   0.04321  -0.0559   1.0000   0.0257
 -10.250  -0.8274   0.04719   0.04019  -0.0530   1.0000   0.0260
 -10.000  -0.8325   0.04460   0.03729  -0.0503   1.0000   0.0263
  -9.750  -0.8342   0.04214   0.03447  -0.0476   1.0000   0.0270
  -9.500  -0.8320   0.03987   0.03189  -0.0452   1.0000   0.0279
  -9.250  -0.8242   0.03816   0.03011  -0.0433   1.0000   0.0291
  -9.000  -0.8151   0.03658   0.02839  -0.0414   1.0000   0.0301
  -8.750  -0.8042   0.03489   0.02651  -0.0394   1.0000   0.0312
  -8.500  -0.7915   0.03314   0.02455  -0.0375   1.0000   0.0324
  -8.250  -0.7774   0.03153   0.02274  -0.0356   1.0000   0.0337
  -8.000  -0.7628   0.03028   0.02123  -0.0337   1.0000   0.0356
  -7.750  -0.7496   0.02886   0.01983  -0.0319   1.0000   0.0377
  -7.500  -0.7359   0.02782   0.01875  -0.0301   1.0000   0.0402
  -7.250  -0.7214   0.02673   0.01758  -0.0282   1.0000   0.0424
  -7.000  -0.7067   0.02574   0.01647  -0.0263   1.0000   0.0450
  -6.750  -0.6935   0.02471   0.01545  -0.0245   1.0000   0.0488
  -6.500  -0.6788   0.02386   0.01458  -0.0229   1.0000   0.0532
  -6.000  -0.6480   0.02216   0.01279  -0.0200   1.0000   0.0642
  -5.750  -0.6196   0.02126   0.01187  -0.0212   0.9966   0.0755
  -5.500  -0.5892   0.02037   0.01101  -0.0228   0.9925   0.0940
  -5.250  -0.5599   0.01935   0.01015  -0.0244   0.9881   0.1282
  -5.000  -0.5304   0.01787   0.00915  -0.0267   0.9842   0.2203
  -4.750  -0.5066   0.01647   0.00902  -0.0275   0.9796   0.4487
  -4.500  -0.4752   0.01662   0.00915  -0.0283   0.9748   0.5129
  -4.250  -0.4412   0.01687   0.00926  -0.0295   0.9709   0.5472
  -4.000  -0.4128   0.01715   0.00946  -0.0295   0.9654   0.5713
  -3.750  -0.3827   0.01752   0.00978  -0.0296   0.9605   0.5938
  -3.500  -0.3505   0.01805   0.01026  -0.0299   0.9568   0.6170
  -3.250  -0.3247   0.01833   0.01049  -0.0292   0.9508   0.6311
  -3.000  -0.2929   0.01824   0.01028  -0.0303   0.9462   0.6372
  -2.750  -0.2585   0.01817   0.01009  -0.0319   0.9429   0.6409
  -2.500  -0.2297   0.01805   0.00986  -0.0325   0.9374   0.6453
  -2.250  -0.1982   0.01790   0.00958  -0.0338   0.9324   0.6504
  -2.000  -0.1642   0.01784   0.00948  -0.0352   0.9289   0.6535
  -1.750  -0.1343   0.01778   0.00935  -0.0359   0.9240   0.6572
  -1.500  -0.1048   0.01770   0.00921  -0.0366   0.9184   0.6620
  -1.250  -0.0703   0.01761   0.00907  -0.0383   0.9148   0.6663
  -1.000  -0.0377   0.01757   0.00901  -0.0394   0.9109   0.6696
  -0.750  -0.0115   0.01755   0.00899  -0.0394   0.9043   0.6738
  -0.500   0.0232   0.01747   0.00888  -0.0411   0.9005   0.6791
  -0.250   0.0597   0.01741   0.00884  -0.0429   0.8978   0.6828
   0.000   0.0821   0.01744   0.00891  -0.0421   0.8899   0.6867
   0.250   0.1165   0.01739   0.00888  -0.0436   0.8859   0.6916
   0.500   0.1531   0.01732   0.00885  -0.0455   0.8831   0.6964
   0.750   0.1751   0.01739   0.00900  -0.0445   0.8747   0.7006
   1.000   0.2094   0.01733   0.00900  -0.0459   0.8705   0.7056
   1.250   0.2386   0.01732   0.00907  -0.0464   0.8643   0.7108
   1.500   0.2679   0.01731   0.00917  -0.0466   0.8579   0.7153
   1.750   0.3047   0.01718   0.00915  -0.0483   0.8539   0.7208
   2.000   0.3289   0.01721   0.00930  -0.0477   0.8442   0.7265
   2.250   0.3656   0.01703   0.00926  -0.0490   0.8391   0.7313
   2.500   0.3918   0.01699   0.00934  -0.0486   0.8281   0.7375
   2.750   0.4220   0.01679   0.00930  -0.0486   0.8168   0.7430
   3.000   0.4540   0.01643   0.00910  -0.0485   0.8013   0.7492
   3.250   0.4864   0.01584   0.00859  -0.0480   0.7731   0.7556
   3.500   0.5156   0.01535   0.00814  -0.0468   0.7339   0.7614
   3.750   0.5418   0.01515   0.00796  -0.0456   0.6887   0.7689
   4.000   0.5658   0.01508   0.00784  -0.0439   0.6219   0.7751
   4.250   0.5853   0.01559   0.00763  -0.0415   0.4659   0.7831
   4.500   0.5924   0.01696   0.00809  -0.0378   0.2941   0.7903
   4.750   0.6043   0.01835   0.00878  -0.0356   0.1644   0.7991
   5.000   0.6203   0.01934   0.00947  -0.0338   0.1095   0.8074
   5.250   0.6385   0.02015   0.01019  -0.0322   0.0864   0.8169
   5.500   0.6572   0.02092   0.01097  -0.0307   0.0740   0.8277
   5.750   0.6747   0.02166   0.01175  -0.0290   0.0647   0.8384
   6.000   0.6925   0.02241   0.01266  -0.0271   0.0588   0.8506
   6.250   0.7101   0.02318   0.01350  -0.0254   0.0536   0.8647
   6.500   0.7277   0.02407   0.01449  -0.0237   0.0490   0.8814
   6.750   0.7474   0.02499   0.01557  -0.0222   0.0457   0.9022
   7.000   0.7704   0.02603   0.01668  -0.0216   0.0425   0.9320
   7.250   0.8001   0.02750   0.01826  -0.0226   0.0391   1.0000
   7.500   0.8280   0.02904   0.01998  -0.0229   0.0365   1.0000
   7.750   0.8551   0.03084   0.02194  -0.0232   0.0346   1.0000
   8.000   0.8792   0.03248   0.02369  -0.0232   0.0327   1.0000
   8.250   0.9017   0.03466   0.02597  -0.0231   0.0309   1.0000
   8.500   0.9216   0.03679   0.02855  -0.0221   0.0293   1.0000
   8.750   0.9386   0.03952   0.03171  -0.0209   0.0283   1.0000
   9.000   0.9514   0.04244   0.03504  -0.0193   0.0276   1.0000
   9.250   0.9599   0.04555   0.03854  -0.0174   0.0270   1.0000
   9.500   0.9645   0.04864   0.04200  -0.0152   0.0265   1.0000
   9.750   0.9671   0.05143   0.04507  -0.0131   0.0259   1.0000
  10.000   0.9718   0.05344   0.04721  -0.0114   0.0250   1.0000
  10.250   0.9709   0.05575   0.04966  -0.0093   0.0244   1.0000
  10.500   0.9654   0.05843   0.05250  -0.0070   0.0240   1.0000
  10.750   0.9499   0.06183   0.05612  -0.0043   0.0237   1.0000
  11.000   0.9314   0.06558   0.06012  -0.0024   0.0236   1.0000
  11.250   0.9115   0.06984   0.06458  -0.0017   0.0236   1.0000
  11.500   0.8913   0.07462   0.06955  -0.0022   0.0236   1.0000
  11.750   0.8696   0.08023   0.07533  -0.0042   0.0237   1.0000
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