EPPLER 66 AIRFOIL (e66-il)
EPPLER 66 AIRFOIL - Eppler E66 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(e66-il) EPPLER 66 AIRFOIL Eppler E66 low Reynolds number airfoil Max thickness 10.1% at 28.7% chord. Max camber 4.1% at 52.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 66 AIRFOIL
33. 29.
0.0002100 -.0015900
0.0015000 0.0046900
0.0075900 0.0125900
0.0180700 0.0212000
0.0328300 0.0300600
0.0518200 0.0388600
0.0749000 0.0473700
0.1019200 0.0553900
0.1326500 0.0627700
0.1668400 0.0693600
0.2041800 0.0750400
0.2443500 0.0797200
0.2869600 0.0833100
0.3316400 0.0857500
0.3779600 0.0870100
0.4255100 0.0870500
0.4738600 0.0858800
0.5225400 0.0835500
0.5711300 0.0801000
0.6191600 0.0756100
0.6662000 0.0702100
0.7117900 0.0640300
0.7555000 0.0572200
0.7968900 0.0499600
0.8355600 0.0424700
0.8711000 0.0349700
0.9030500 0.0277200
0.9309800 0.0209200
0.9544100 0.0146600
0.9732000 0.0089300
0.9874300 0.0041100
0.9967000 0.0010200
1.0000000 0.0000000
0.0002100 -.0015900
0.0045700 -.0067400
0.0146400 -.0116200
0.0297700 -.0158200
0.0498700 -.0191200
0.0748400 -.0214200
0.1045400 -.0227200
0.1387600 -.0230500
0.1772400 -.0224700
0.2196100 -.0211000
0.2654700 -.0190500
0.3143500 -.0164600
0.3657200 -.0134600
0.4190000 -.0102100
0.4735900 -.0068400
0.5288500 -.0035000
0.5841200 -.0003300
0.6387100 0.0025500
0.6919300 0.0050000
0.7430900 0.0069200
0.7914800 0.0082300
0.8364200 0.0088500
0.8772300 0.0087600
0.9132600 0.0079700
0.9438500 0.0064800
0.9682900 0.0044300
0.9859300 0.0022700
0.9964900 0.0006200
1.0000000 0.0000000
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Polars for EPPLER 66 AIRFOIL (e66-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e66-il | 50,000 | 9 | 40.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 50,000 | 5 | 40.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 100,000 | 9 | 64.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 100,000 | 5 | 63.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 200,000 | 9 | 91.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 200,000 | 5 | 86.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 500,000 | 9 | 128.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 500,000 | 5 | 113.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 1,000,000 | 9 | 153.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 1,000,000 | 5 | 121.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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