Add to ORKGThe shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic characteristics of two-dimensional supersonic airfoils. A discussion is given of the effect of thickness ratio, free-stream Mach number, angle of attack, camber, thickness distribution, and aileron deflection. The calculations indicated that the minimum drag of supersonic airfoils is obtained when the maximum thickness is behind the 0.50 chord. The center of pressure obtained for a symmetrical supersonic airfoil was found to be ahead of the 0.50 chord
An investigation of the characteristics of a wing with an aspect ratio of 9.0 and an NACA 65-210 air...
A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl ai...
The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at su...
The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic c...
A theoretical investigation is made of the airfoil profile for minimum pressure drag at zero lift in...
Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to...
Two-dimensional tests of eight 6-percent-thick symmetrical airfoils of the supersonic and subsonic t...
Fundamental investigations of compressibility phenomena for airfoils have shown that serious adverse...
A two-dimensional wind-tunnel investigation of the flow and force characteristics of four NACA 6A-se...
Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to...
A preliminary theoretical and experimental investigation has been made on the aerodynamic characteri...
An analysis has been made of available experimental data to show the effects of most of the variable...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
An investigation has been conducted to determine the aerodynamic characteristics of a group of NACA ...
Six, 3-inch-chord symmetrical airfoil sections having systematic variations in thickness and thickne...
An investigation of the characteristics of a wing with an aspect ratio of 9.0 and an NACA 65-210 air...
A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl ai...
The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at su...
The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic c...
A theoretical investigation is made of the airfoil profile for minimum pressure drag at zero lift in...
Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to...
Two-dimensional tests of eight 6-percent-thick symmetrical airfoils of the supersonic and subsonic t...
Fundamental investigations of compressibility phenomena for airfoils have shown that serious adverse...
A two-dimensional wind-tunnel investigation of the flow and force characteristics of four NACA 6A-se...
Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to...
A preliminary theoretical and experimental investigation has been made on the aerodynamic characteri...
An analysis has been made of available experimental data to show the effects of most of the variable...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
An investigation has been conducted to determine the aerodynamic characteristics of a group of NACA ...
Six, 3-inch-chord symmetrical airfoil sections having systematic variations in thickness and thickne...
An investigation of the characteristics of a wing with an aspect ratio of 9.0 and an NACA 65-210 air...
A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl ai...
The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at su...