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
Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain a...
A summary has been made of available data on the characteristics of airfoil sections with trailing-e...
An investigation has been made in the Langley two-dimensional low-turbulence tunnel and in the Langl...
Lift and pitching-moment characteristics of an NACA 0006 airfoil are presented for various deflectio...
The results are presented of a two-dimensional investigation conducted to determine the effect of bl...
This report contains the results of a high-speed wind-tunnel investigation of the effectiveness of a...
This report deals with pressure distribution tests on an airfoil with a conventional trailing edge f...
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 Langley two-dimensional low-turbulence tunnel and in the Langl...
Wind tunnel measurements of pressure distributions on wing having NACA 4415 airfoil sections with tr...
An analysis has been made of the lift-control effectiveness of a 20-percent-chord plain trailing-edg...
Pressure-distribution tests of an N.A.C.A. 0009 airfoil with a 50-percent-chord plain flap and three...
As part of a general investigation in the NACA 19-foot pressure tunnel to determine stall characteri...
An analysis has been made of the lift control effectiveness of a 20-percent-chord plain trailing-edg...
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-c...
Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain a...
A summary has been made of available data on the characteristics of airfoil sections with trailing-e...
An investigation has been made in the Langley two-dimensional low-turbulence tunnel and in the Langl...
Lift and pitching-moment characteristics of an NACA 0006 airfoil are presented for various deflectio...
The results are presented of a two-dimensional investigation conducted to determine the effect of bl...
This report contains the results of a high-speed wind-tunnel investigation of the effectiveness of a...
This report deals with pressure distribution tests on an airfoil with a conventional trailing edge f...
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 Langley two-dimensional low-turbulence tunnel and in the Langl...
Wind tunnel measurements of pressure distributions on wing having NACA 4415 airfoil sections with tr...
An analysis has been made of the lift-control effectiveness of a 20-percent-chord plain trailing-edg...
Pressure-distribution tests of an N.A.C.A. 0009 airfoil with a 50-percent-chord plain flap and three...
As part of a general investigation in the NACA 19-foot pressure tunnel to determine stall characteri...
An analysis has been made of the lift control effectiveness of a 20-percent-chord plain trailing-edg...
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-c...
Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain a...
A summary has been made of available data on the characteristics of airfoil sections with trailing-e...
An investigation has been made in the Langley two-dimensional low-turbulence tunnel and in the Langl...