EPPLER 1233 AIRFOIL (e1233-il)
EPPLER 1233 AIRFOIL - Eppler E1233 general aviation airfoil
| Details | Dat file | Parser | |
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(e1233-il) EPPLER 1233 AIRFOIL Eppler E1233 general aviation airfoil Max thickness 18.9% at 29.8% chord. Max camber 4.4% at 29.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 1233 AIRFOIL
52.0 46.0
0.0000200 -.0010300
0.0006600 0.0058100
0.0029600 0.0133100
0.0106100 0.0293400
0.0171700 0.0383900
0.0252400 0.0475700
0.0347800 0.0567600
0.0457600 0.0658900
0.0581400 0.0748600
0.0718600 0.0835700
0.0868800 0.0919500
0.1031200 0.0999100
0.1205300 0.1073600
0.1390400 0.1141800
0.1586300 0.1202500
0.1792900 0.1254900
0.2010200 0.1298500
0.2237900 0.1332800
0.2476100 0.1357500
0.2724600 0.1372700
0.2983000 0.1378700
0.3250900 0.1375700
0.3527800 0.1364400
0.3812900 0.1345400
0.4105000 0.1319200
0.4403200 0.1286400
0.4706300 0.1247700
0.5013200 0.1203600
0.5322600 0.1154800
0.5633200 0.1102000
0.5943700 0.1045800
0.6252500 0.0987000
0.6558200 0.0926200
0.6859400 0.0864000
0.7154500 0.0801100
0.7441900 0.0738000
0.7720200 0.0675200
0.7987800 0.0613300
0.8243200 0.0552600
0.8485000 0.0493500
0.8711900 0.0436400
0.8922400 0.0381300
0.9115400 0.0328400
0.9289800 0.0277800
0.9444200 0.0229000
0.9578700 0.0180700
0.9695200 0.0132900
0.9795400 0.0088000
0.9879100 0.0049700
0.9943800 0.0021400
0.9985500 0.0005100
1.0000000 0.0000000
0.0000200 -.0010300
0.0012600 -.0067500
0.0050700 -.0116500
0.0115400 -.0164100
0.0201500 -.0210200
0.0307700 -.0253800
0.0433400 -.0293700
0.0578900 -.0329400
0.0744100 -.0361300
0.0928400 -.0389800
0.1130900 -.0415200
0.1350500 -.0437800
0.1586000 -.0457500
0.1836100 -.0474500
0.2099700 -.0488700
0.2375300 -.0500000
0.2661700 -.0508400
0.2957400 -.0513900
0.3261000 -.0516200
0.3571100 -.0515300
0.3886100 -.0511000
0.4204500 -.0503100
0.4524900 -.0491000
0.4846000 -.0473900
0.5167400 -.0451600
0.5488400 -.0423900
0.5808300 -.0391200
0.6126400 -.0353700
0.6441900 -.0311600
0.6754700 -.0264800
0.7066000 -.0215000
0.7374900 -.0165400
0.7679100 -.0118600
0.7975900 -.0076200
0.8262600 -.0039500
0.8536400 -.0009300
0.8794400 0.0013700
0.9034000 0.0029400
0.9252400 0.0038000
0.9446800 0.0039700
0.9614400 0.0035700
0.9753000 0.0027800
0.9861200 0.0018300
0.9938400 0.0009200
0.9984600 0.0002500
1.0000000 0.0000000
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Polars for EPPLER 1233 AIRFOIL (e1233-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1233-il | 50,000 | 9 | 15.7 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 50,000 | 5 | 21.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 9 | 34 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 5 | 41.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 9 | 56.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 5 | 58.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 9 | 81 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 5 | 81.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 9 | 104.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 5 | 103.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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