Add to ORKGReport presenting an investigation in the 7- by 10-foot wind tunnel of the effects of various modifications to the profile of a 0.20-chord plain sealed aileron and a 0.15-chord plain sealed aileron on an NACA 66,2-216 airfoil. Thickening of the aileron was found to reduce the aileron effectiveness, reduce the slope of the wing section lift curve, and reduce the hinge-moment coefficients. Results regarding the section data, aileron effectiveness, aileron hinge moments, lift, pitching moment, drag, and Reynolds number are provided
An invtxtigaiion has been made to dd.ermine the eJect of control-swface projile modwio-na on the aer...
Compressibilit:y effects on.the aerodynanic section characteristics of an airfoil with a round-nose ...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of modifications ...
An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1....
Ailerons having a beveled trailing edge and a blunt-nose overhang of 35 percent aileron chord on an ...
A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section...
This investigation was carried out for the purpose of determining the effectiveness of ailerons and ...
Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test sec...
An investigation was made in the LMAL 7- by 10-foot tunnel of various modifications to the trailing ...
The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is chara...
Wind-tunnel measurements of the pressure distribution were made on a semispan wing tith a modified N...
An investigation has "been made of the two-dimensional aerodynamic characteristics of three air...
An invtxtigaiion has been made to dd.ermine the eJect of control-swface projile modwio-na on the aer...
Compressibilit:y effects on.the aerodynanic section characteristics of an airfoil with a round-nose ...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of modifications ...
An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1....
Ailerons having a beveled trailing edge and a blunt-nose overhang of 35 percent aileron chord on an ...
A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section...
This investigation was carried out for the purpose of determining the effectiveness of ailerons and ...
Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test sec...
An investigation was made in the LMAL 7- by 10-foot tunnel of various modifications to the trailing ...
The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is chara...
Wind-tunnel measurements of the pressure distribution were made on a semispan wing tith a modified N...
An investigation has "been made of the two-dimensional aerodynamic characteristics of three air...
An invtxtigaiion has been made to dd.ermine the eJect of control-swface projile modwio-na on the aer...
Compressibilit:y effects on.the aerodynanic section characteristics of an airfoil with a round-nose ...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...