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DFVLR R-4 AIRFOIL (dfvlrr4-il)

DFVLR R-4 AIRFOIL - DFVLR R-4 transonic airfoil


Airfoil dfvlrr4-il
Details Dat file Parser  
(dfvlrr4-il) DFVLR R-4 AIRFOIL
DFVLR R-4 transonic airfoil
Max thickness 13.4% at 37.9% chord.
Max camber 2.1% at 79.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 DFVLR R-4 AIRFOIL
       71.       69.

 0.0       0.0
 0.0000370 0.0043010
 0.0004076 0.0063066
 0.0009840 0.0079153
 0.0014634 0.0093224
 0.0019486 0.0103296
 0.0042938 0.0140644
 0.0092091 0.0198370
 0.0141449 0.0242098
 0.0190909 0.0278827
 0.0240471 0.0308556
 0.0290063 0.0336285
 0.0339714 0.0360015
 0.0389394 0.0381746
 0.0439132 0.0399476
 0.0488885 0.0416207
 0.0538667 0.0430938
 0.0588465 0.0444669
 0.0638261 0.0458399
 0.0688087 0.0470131
 0.0787770 0.0491594
 0.0987206 0.0529519
 0.1186717 0.0562446
 0.1386300 0.0590373
 0.1586928 0.0615315
 0.1786599 0.0637242
 0.1986300 0.0657170
 0.2186030 0.0675098
 0.2385804 0.0690026
 0.2585592 0.0703955
 0.2785410 0.0715883
 0.2985242 0.0726812
 0.3185119 0.0734741
 0.3386009 0.0741684
 0.3585917 0.0747615
 0.3785851 0.0751544
 0.3875828 0.0752862
 0.3985800 0.0754474
 0.4185765 0.0756404
 0.4385759 0.0756333
 0.4585767 0.0755263
 0.4785790 0.0753194
 0.4985843 0.0749124
 0.5185909 0.0744055
 0.5386991 0.0738000
 0.5587102 0.0729931
 0.5787228 0.0720862
 0.5987382 0.0709793
 0.6187566 0.0696724
 0.6387780 0.0681655
 0.6588023 0.0664588
 0.6788309 0.0644520
 0.6988640 0.0621453
 0.7190014 0.0595400
 0.7390418 0.0567334
 0.7590850 0.0537267
 0.7791313 0.0505200
 0.7991804 0.0471134
 0.8192326 0.0435068
 0.8392890 0.0396003
 0.8593455 0.0356937
 0.8794064 0.0314871
 0.8994688 0.0271806
 0.9196326 0.0227755
 0.9397007 0.0180690
 0.9597704 0.0132626
 0.9798445 0.0081561
 0.9848638 0.0068295
 0.9898830 0.0055029
 0.9949023 0.0041763
 1.0000000 0.0025497

 0.0       0.0
 0.0005277 -.0018925
 0.0011481 -.0032835
 0.0023814 -.0055657
 0.0046219 -.0083332
 0.0096822 -.0124595
 0.0147263 -.0154859
 0.0197646 -.0181124
 0.0247970 -.0203389
 0.0298251 -.0222654
 0.0348502 -.0239920
 0.0398738 -.0256186
 0.0448960 -.0271452
 0.0499152 -.0284718
 0.0549345 -.0297984
 0.0599523 -.0310250
 0.0649685 -.0321516
 0.0699848 -.0332782
 0.0749997 -.0343049
 0.0800131 -.0352315
 0.1000667 -.0389381
 0.1201128 -.0421448
 0.1401533 -.0449515
 0.1602907 -.0475567
 0.1803238 -.0498634
 0.2003524 -.0518703
 0.2203782 -.0536771
 0.2403995 -.0551839
 0.2604177 -.0564907
 0.2804319 -.0574976
 0.3004430 -.0583045
 0.3204481 -.0587114
 0.3405503 -.0589170
 0.3605499 -.0589240
 0.3805448 -.0586310
 0.4005368 -.0581381
 0.4205244 -.0573451
 0.4405106 -.0564523
 0.4604939 -.0553594
 0.4804743 -.0540665
 0.4904629 -.0533201
 0.5054460 -.0522005
 0.5255190 -.0504062
 0.5454890 -.0484134
 0.5654562 -.0462206
 0.5854205 -.0438279
 0.6053802 -.0411352
 0.6253356 -.0381426
 0.6452882 -.0349499
 0.6652364 -.0314573
 0.6851801 -.0276647
 0.7051194 -.0235722
 0.7251601 -.0195781
 0.7450994 -.0154855
 0.7650403 -.0114930
 0.7849840 -.0077004
 0.8049306 -.0041078
 0.8248845 -.0010151
 0.8448443 0.0016776
 0.8648143 0.0036704
 0.8847933 0.0050632
 0.9048809 0.0058576
 0.9248788 0.0059506
 0.9448869 0.0053437
 0.9649112 0.0036369
 0.9849546 0.0006302
 0.9899694 -.0003965
 0.9949858 -.0015231
 1.0000000 -.0025497
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Polars for DFVLR R-4 AIRFOIL (dfvlrr4-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   dfvlrr4-il50,000926.7 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   dfvlrr4-il50,000525.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   dfvlrr4-il100,000933.6 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dfvlrr4-il100,000533.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   dfvlrr4-il200,000946.3 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   dfvlrr4-il200,000547.9 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   dfvlrr4-il500,000972.9 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dfvlrr4-il500,000566.2 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   dfvlrr4-il1,000,000987.1 at α=0.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dfvlrr4-il1,000,000582.9 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
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