Add to ORKGThe results of an investigation of the effect of support interference on airfoil drag data obtained in the variable-density tunnel are presented. As a result of the support interference, previously published airfoil data from the variable-density tunnel have shown too large drag coefficients and too large a rate of increase of drag coefficients and too large a rate increase of drag coefficients with airfoil thickness. The practical effect of the corrections on the choice of the optimum section is briefly considered and corrected data for a selected list of airfoils are presented as a convenience to the designer. Methods of correcting published data for other airfoils are presented
In order to give the large-scale characteristics of a variety of airfoils in a form which will be of...
Report presents the results of an investigation conducted in the NACA 7 by 10-foot win tunnel to det...
This report presents the results of an investigation conducted in the NACA full-scale wind tunnel to...
The results of an investigation of the effect of support interference on airfoil drag data obtained ...
An investigation of the interference associated with tail surfaces added to wing-fuselage combinatio...
The historical development of NACA airfoils is briefly reviewed. New data are presented that permit ...
The aerodynamic characteristics of a large number of miscellaneous airfoils tested in the variable-d...
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-c...
Pressure distributions determined from high-speed wind-tunnel tests are presented for five NACA airf...
This report presents the results of tests of 209 simple wing-fuselage combinations made in the NACA ...
In connection with the interference program being conducted in the NACA variable-density wind tunnel...
An investigation of a large group of related airfoils was made in the NACA variable-density wind tun...
Fundamental investigations of compressibility phenomena for airfoils have shown that serious adverse...
An investigation has been made to determine the effect of control-surface profile modifications on t...
Three groups of airfoils have been tested in the variable density wind tunnel. The first group conta...
In order to give the large-scale characteristics of a variety of airfoils in a form which will be of...
Report presents the results of an investigation conducted in the NACA 7 by 10-foot win tunnel to det...
This report presents the results of an investigation conducted in the NACA full-scale wind tunnel to...
The results of an investigation of the effect of support interference on airfoil drag data obtained ...
An investigation of the interference associated with tail surfaces added to wing-fuselage combinatio...
The historical development of NACA airfoils is briefly reviewed. New data are presented that permit ...
The aerodynamic characteristics of a large number of miscellaneous airfoils tested in the variable-d...
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-c...
Pressure distributions determined from high-speed wind-tunnel tests are presented for five NACA airf...
This report presents the results of tests of 209 simple wing-fuselage combinations made in the NACA ...
In connection with the interference program being conducted in the NACA variable-density wind tunnel...
An investigation of a large group of related airfoils was made in the NACA variable-density wind tun...
Fundamental investigations of compressibility phenomena for airfoils have shown that serious adverse...
An investigation has been made to determine the effect of control-surface profile modifications on t...
Three groups of airfoils have been tested in the variable density wind tunnel. The first group conta...
In order to give the large-scale characteristics of a variety of airfoils in a form which will be of...
Report presents the results of an investigation conducted in the NACA 7 by 10-foot win tunnel to det...
This report presents the results of an investigation conducted in the NACA full-scale wind tunnel to...