lrn1007 (lrn1007-il)
lrn1007 - LRN(1)-1007 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(lrn1007-il) lrn1007 LRN(1)-1007 low Reynolds number airfoil Max thickness 7.3% at 39.8% chord. Max camber 5.9% at 44.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
lrn1007
1.00000 0.000000
0.960500 0.780000E-02
0.920500 0.162000E-01
0.880500 0.250900E-01
0.840500 0.346700E-01
0.800500 0.449800E-01
0.760500 0.558500E-01
0.720500 0.667900E-01
0.680500 0.760800E-01
0.636860 0.828000E-01
0.589750 0.883700E-01
0.541950 0.920300E-01
0.493840 0.943300E-01
0.445770 0.952700E-01
0.398180 0.949100E-01
0.351520 0.933400E-01
0.306280 0.905600E-01
0.262880 0.866600E-01
0.221760 0.816700E-01
0.183300 0.757000E-01
0.147860 0.688100E-01
0.115730 0.611300E-01
0.872200E-01 0.528100E-01
0.625200E-01 0.440000E-01
0.418300E-01 0.349200E-01
0.262600E-01 0.263500E-01
0.128800E-01 0.169000E-01
0.471000E-02 0.864000E-02
0.500000E-03 0.240000E-02
0.000000 0.000000
0.500000E-03 0.500000E-04
0.471000E-02 0.100000E-02
0.128800E-01 0.322000E-02
0.262600E-01 0.646000E-02
0.418300E-01 0.922000E-02
0.625200E-01 0.122500E-01
0.872200E-01 0.149900E-01
0.115730 0.170300E-01
0.147860 0.186300E-01
0.183300 0.194800E-01
0.221760 0.200900E-01
0.262880 0.205200E-01
0.306280 0.208100E-01
0.351520 0.215100E-01
0.398180 0.221700E-01
0.445770 0.227700E-01
0.493840 0.231000E-01
0.541950 0.235400E-01
0.589750 0.237800E-01
0.636960 0.235300E-01
0.680500 0.224200E-01
0.720500 0.206700E-01
0.760500 0.183900E-01
0.800500 0.159500E-01
0.840500 0.128600E-01
0.880500 0.972000E-02
0.920500 0.649000E-02
0.960500 0.320000E-02
1.00000 0.000000
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Similar airfoils
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Polars for lrn1007 (lrn1007-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lrn1007-il | 50,000 | 9 | 30.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 50,000 | 5 | 35.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 100,000 | 9 | 51.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 100,000 | 5 | 55.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 200,000 | 9 | 81.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 200,000 | 5 | 98.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 500,000 | 9 | 125.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 500,000 | 5 | 150.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 1,000,000 | 9 | 127.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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