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CURTISS CR-1 AIRFOIL (cr1-il)

CURTISS CR-1 AIRFOIL - Curtiss CR-1 general aviation airfoil


Airfoil cr1-il
Details Dat file Parser  
(cr1-il) CURTISS CR-1 AIRFOIL
Curtiss CR-1 general aviation airfoil
Max thickness 12.2% at 24% chord.
Max camber 4.7% at 42% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 CURTISS CR-1 AIRFOIL                                                           
      61.0      61.0
 
 0.0000000 0.0000000
 0.0005000 0.0028877
 0.0010000 0.0045082
 0.0020000 0.0069026
 0.0040000 0.0104752
 0.0080000 0.0159130
 0.0120000 0.0204608
 0.0200000 0.0284739
 0.0300000 0.0372190
 0.0400000 0.0449223
 0.0500000 0.0515424
 0.0600000 0.0571529
 0.0800000 0.0667125
 0.1000000 0.0748305
 0.1200000 0.0811676
 0.1400000 0.0861657
 0.1600000 0.0903037
 0.1800000 0.0938086
 0.2000000 0.0967598
 0.2200000 0.0992238
 0.2400000 0.1012466
 0.2600000 0.1028692
 0.2800000 0.1041314
 0.3000000 0.1050716
 0.3200000 0.1057211
 0.3400000 0.1060956
 0.3600000 0.1062082
 0.3800000 0.1060724
 0.4000000 0.1057010
 0.4200000 0.1051022
 0.4400000 0.1042715
 0.4600000 0.1032027
 0.4800000 0.1018895
 0.5000000 0.1003252
 0.5200000 0.0985024
 0.5400000 0.0964112
 0.5600000 0.0940411
 0.5800000 0.0913811
 0.6000000 0.0884199
 0.6200000 0.0851617
 0.6400000 0.0816512
 0.6600000 0.0779406
 0.6800000 0.0740830
 0.7000000 0.0701324
 0.7200000 0.0661238
 0.7400000 0.0620373
 0.7600000 0.0578435
 0.7800000 0.0535129
 0.8000000 0.0490156
 0.8200000 0.0443404
 0.8400000 0.0395362
 0.8600000 0.0346645
 0.8800000 0.0297881
 0.9000000 0.0249688
 0.9200000 0.0202277
 0.9400000 0.0154453
 0.9600000 0.0104761
 0.9700000 0.0079079
 0.9800000 0.0052997
 0.9900000 0.0026651
 1.0000000 0.0000173
 
 0.0000000 0.0000000
 0.0005000 -.0049013
 0.0010000 -.0063669
 0.0020000 -.0084885
 0.0040000 -.0115467
 0.0080000 -.0158525
 0.0120000 -.0190076
 0.0200000 -.0232770
 0.0300000 -.0265473
 0.0400000 -.0288161
 0.0500000 -.0303860
 0.0600000 -.0314227
 0.0800000 -.0322357
 0.1000000 -.0319040
 0.1200000 -.0310798
 0.1400000 -.0298930
 0.1600000 -.0283204
 0.1800000 -.0264458
 0.2000000 -.0244737
 0.2200000 -.0225857
 0.2400000 -.0208260
 0.2600000 -.0192004
 0.2800000 -.0177150
 0.3000000 -.0163755
 0.3200000 -.0151843
 0.3400000 -.0141278
 0.3600000 -.0131887
 0.3800000 -.0123493
 0.4000000 -.0115922
 0.4200000 -.0109030
 0.4400000 -.0102799
 0.4600000 -.0097239
 0.4800000 -.0092366
 0.5000000 -.0088192
 0.5200000 -.0084708
 0.5400000 -.0081817
 0.5600000 -.0079399
 0.5800000 -.0077333
 0.6000000 -.0075498
 0.6200000 -.0073791
 0.6400000 -.0072182
 0.6600000 -.0070659
 0.6800000 -.0069210
 0.7000000 -.0067822
 0.7200000 -.0066495
 0.7400000 -.0065270
 0.7600000 -.0064199
 0.7800000 -.0063335
 0.8000000 -.0062730
 0.8200000 -.0062355
 0.8400000 -.0061851
 0.8600000 -.0060768
 0.8800000 -.0058660
 0.9000000 -.0055081
 0.9200000 -.0049546
 0.9400000 -.0041417
 0.9600000 -.0030058
 0.9700000 -.0023222
 0.9800000 -.0015842
 0.9900000 -.0008099
 1.0000000 -.0000173
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Lednicer format dat file
Selig format dat file

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Polars for CURTISS CR-1 AIRFOIL (cr1-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   cr1-il50,000922.7 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   cr1-il50,000532.4 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   cr1-il100,000954.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   cr1-il100,000553 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   cr1-il200,000979.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   cr1-il200,000572.9 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   cr1-il500,0009109.5 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   cr1-il500,000589.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   cr1-il1,000,0009120.9 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   cr1-il1,000,0005104.3 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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