Add to ORKGLift and pitching-moment characteristics of an NACA 0006 airfoil are presented for various deflections of a 0.15-chord leading-edge flap and a 0.30-chord plain trailing-edge flap. Pressure-distribution data are presented in tabular form. The data were obtained at a Mach number of 0.15 and a Reynolds number of 4,500,000
AN investigation was made of a large-chord NACA 23030 airfoil with a 40- and a 25.66 percent-chord s...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is chara...
Lift and pitching-moment characteristics of an NACA 0006 airfoil are presented for various deflectio...
Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil sec...
From Summary: "Pressure distributions determined from high-speed wind-tunnel tests are presented for...
Pressure-distribution tests of an NACA 0009 airfoil with an 80-percent-chord plain flap and three pl...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 air...
Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at t...
An investigation was conducted in a low-turbulence pressure tunnel to determine the two-dimensional ...
This report deals with pressure distribution tests on an airfoil with a conventional trailing edge f...
An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic char...
"This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds inc...
Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps....
Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, ...
AN investigation was made of a large-chord NACA 23030 airfoil with a 40- and a 25.66 percent-chord s...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is chara...
Lift and pitching-moment characteristics of an NACA 0006 airfoil are presented for various deflectio...
Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil sec...
From Summary: "Pressure distributions determined from high-speed wind-tunnel tests are presented for...
Pressure-distribution tests of an NACA 0009 airfoil with an 80-percent-chord plain flap and three pl...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 air...
Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at t...
An investigation was conducted in a low-turbulence pressure tunnel to determine the two-dimensional ...
This report deals with pressure distribution tests on an airfoil with a conventional trailing edge f...
An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic char...
"This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds inc...
Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps....
Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, ...
AN investigation was made of a large-chord NACA 23030 airfoil with a 40- and a 25.66 percent-chord s...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is chara...