Add to ORKGThe present report is a description of systematic tests at maximum lift on airfoils with and without split flap and of profile drag at low lift. In order to obtain an opinion as to the suitability of the airfoils with flaps, the maximum-lift measurements were repeated on airfoils with split flaps. The profile drag at low lift was arrived at by direct weighing and momentum measurements and, since the profiles were of unusual depth, extended to large Reynolds numbers
The effects of Mach numbers up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coeff...
An analysis has been made of the lift control effectiveness of a 20-percent-chord plain trailing-edg...
"This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds inc...
We have investigated the maximum lift obtainable with slotted airfoils derived from a symmetrical ai...
An investigation was conducted in the NACA 19-foot pressure wind tunnel of a rectangular wing having...
The present report is a description of systematic tests at maximum lift on airfoils with and without...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 air...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
An investigation was conducted in the NACA full-scale wind tunnel to determine the aerodynamic chara...
Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment me...
Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil sec...
The effects of Mach numbers up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coeff...
An analysis has been made of the lift control effectiveness of a 20-percent-chord plain trailing-edg...
"This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds inc...
We have investigated the maximum lift obtainable with slotted airfoils derived from a symmetrical ai...
An investigation was conducted in the NACA 19-foot pressure wind tunnel of a rectangular wing having...
The present report is a description of systematic tests at maximum lift on airfoils with and without...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 air...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
An investigation was conducted in the NACA full-scale wind tunnel to determine the aerodynamic chara...
Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment me...
Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil sec...
The effects of Mach numbers up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coeff...
An analysis has been made of the lift control effectiveness of a 20-percent-chord plain trailing-edg...
"This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds inc...