EPPLER 694 AIRFOIL (e694-il)
EPPLER 694 AIRFOIL - Eppler E694 sailplane airfoil
| Details | Dat file | Parser | |
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(e694-il) EPPLER 694 AIRFOIL Eppler E694 sailplane airfoil Max thickness 15.4% at 40.4% chord. Max camber 4.9% at 59.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 694 AIRFOIL
33.0 29.0
0.0002300 0.0021800
0.0046900 0.0111300
0.0136300 0.0214100
0.0269200 0.0323900
0.0444500 0.0436900
0.0660800 0.0549900
0.0916600 0.0660300
0.1209500 0.0765800
0.1537300 0.0864600
0.1896800 0.0954800
0.2284800 0.1033200
0.2697500 0.1104300
0.3131000 0.1161200
0.3581000 0.1204900
0.4043100 0.1234700
0.4512500 0.1250200
0.4984400 0.1250600
0.5454100 0.1236000
0.5916500 0.1205400
0.6366800 0.1158700
0.6799600 0.1090900
0.7224600 0.0999900
0.7639900 0.0906900
0.8020200 0.0811200
0.8369900 0.0694300
0.8702300 0.0567400
0.9010000 0.0445000
0.9283500 0.0331300
0.9517200 0.0226300
0.9711000 0.0132500
0.9863200 0.0058800
0.9964000 0.0014200
1.0000000 0.0000000
0.0002300 0.0021800
0.0014600 -.0046600
0.0090800 -.0102200
0.0224900 -.0153900
0.0413500 -.0198900
0.0654400 -.0236700
0.0945500 -.0267300
0.1283400 -.0291500
0.1664000 -.0309600
0.2082300 -.0322200
0.2532500 -.0328900
0.3009900 -.0328600
0.3509900 -.0321700
0.4026800 -.0309300
0.4553400 -.0291200
0.5084000 -.0266100
0.5614800 -.0234300
0.6138900 -.0198200
0.6647200 -.0155600
0.7138400 -.0100000
0.7617700 -.0033400
0.8086200 0.0033600
0.8538200 0.0087500
0.8959600 0.0116100
0.9331000 0.0114100
0.9630900 0.0084500
0.9841400 0.0043200
0.9961500 0.0011400
1.0000000 0.0000000
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Polars for EPPLER 694 AIRFOIL (e694-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e694-il | 50,000 | 9 | 25.3 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e694-il | 50,000 | 5 | 21.4 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e694-il | 100,000 | 9 | 40.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e694-il | 100,000 | 5 | 36.4 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e694-il | 200,000 | 9 | 61.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e694-il | 200,000 | 5 | 59.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e694-il | 500,000 | 9 | 113.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e694-il | 500,000 | 5 | 111.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e694-il | 1,000,000 | 9 | 155.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e694-il | 1,000,000 | 5 | 147 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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