Add to ORKGTests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag
Pressure-distribution tests were conducted in the full-scale wind tunnel on a 2:1 tapered U.S.A. 45 ...
An investigation was conducted in the NACA 19-foot pressure wind tunnel of a rectangular wing having...
Aerodynamic force tests of an NACA 23018 airfoil with a Gwinn flap having a chord 25 percent of the ...
Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil sec...
An investigation was made in the NACA 7- by 10-foot wind tunnel to determine the effect of slot-lip ...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 air...
The present report is a description of systematic tests at maximum lift on airfoils with and without...
Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-...
An investigation has been made in the Langley two-dimensional low-turbulence tunnel and in the Langl...
AN investigation was made of a large-chord NACA 23030 airfoil with a 40- and a 25.66 percent-chord s...
An investigation was conducted in a low-turbulence pressure tunnel to determine the two-dimensional ...
An investigation was made in the 7 by 10-foot wind tunnel and in the variable-density wind tunnel of...
Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps....
This report deals with pressure distribution tests on an airfoil with a conventional trailing edge f...
Pressure-distribution tests of an N.A.C.A. 0009 airfoil with a 50-percent-chord plain flap and three...
Pressure-distribution tests were conducted in the full-scale wind tunnel on a 2:1 tapered U.S.A. 45 ...
An investigation was conducted in the NACA 19-foot pressure wind tunnel of a rectangular wing having...
Aerodynamic force tests of an NACA 23018 airfoil with a Gwinn flap having a chord 25 percent of the ...
Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil sec...
An investigation was made in the NACA 7- by 10-foot wind tunnel to determine the effect of slot-lip ...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 air...
The present report is a description of systematic tests at maximum lift on airfoils with and without...
Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-...
An investigation has been made in the Langley two-dimensional low-turbulence tunnel and in the Langl...
AN investigation was made of a large-chord NACA 23030 airfoil with a 40- and a 25.66 percent-chord s...
An investigation was conducted in a low-turbulence pressure tunnel to determine the two-dimensional ...
An investigation was made in the 7 by 10-foot wind tunnel and in the variable-density wind tunnel of...
Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps....
This report deals with pressure distribution tests on an airfoil with a conventional trailing edge f...
Pressure-distribution tests of an N.A.C.A. 0009 airfoil with a 50-percent-chord plain flap and three...
Pressure-distribution tests were conducted in the full-scale wind tunnel on a 2:1 tapered U.S.A. 45 ...
An investigation was conducted in the NACA 19-foot pressure wind tunnel of a rectangular wing having...
Aerodynamic force tests of an NACA 23018 airfoil with a Gwinn flap having a chord 25 percent of the ...