Add to ORKGLift, drag, internal flow, and pressure distribution measurements were made on a low-drag airfoil incorporating various air inlet designs. Two leading-edge air inlets are developed which feature higher lift coefficients and critical Mach than the basic airfoil. Higher lift coefficients and critical speeds are obtained for leading half of these inlet sections but because of high suction pressures near exist, slightly lower critical speeds are obtained for the entire inlet section than the basic airfoil
The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is chara...
Results of flight tests indicate that profile-drag coefficients which were obtained with the low-dra...
Installation of the wing-root inlet was accomplished with no significant effects on the force charac...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
"This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds inc...
Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-...
Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections ...
From Summary: "Pressure distributions determined from high-speed wind-tunnel tests are presented for...
The present report is a description of systematic tests at maximum lift on airfoils with and without...
An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic char...
The lift, drag, and center of pressure characteristics of a model of the Fowler variable-area wing w...
An investigation has been conducted in the Langley two-dimensional low--turbulence pressure tunnel t...
Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA...
An investigation was conducted in a low-turbulence pressure tunnel to determine the two-dimensional ...
Aerodynamic analysis of a low Reynolds number airfoil is critical for numerous applications in the f...
The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is chara...
Results of flight tests indicate that profile-drag coefficients which were obtained with the low-dra...
Installation of the wing-root inlet was accomplished with no significant effects on the force charac...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
"This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds inc...
Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-...
Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections ...
From Summary: "Pressure distributions determined from high-speed wind-tunnel tests are presented for...
The present report is a description of systematic tests at maximum lift on airfoils with and without...
An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic char...
The lift, drag, and center of pressure characteristics of a model of the Fowler variable-area wing w...
An investigation has been conducted in the Langley two-dimensional low--turbulence pressure tunnel t...
Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA...
An investigation was conducted in a low-turbulence pressure tunnel to determine the two-dimensional ...
Aerodynamic analysis of a low Reynolds number airfoil is critical for numerous applications in the f...
The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is chara...
Results of flight tests indicate that profile-drag coefficients which were obtained with the low-dra...
Installation of the wing-root inlet was accomplished with no significant effects on the force charac...