Add to ORKGSlender body methods were applied to some specialized problems associated with missile configurations with elliptic cross sections. Expressions are derived for computing the velocity distribution on the nose section when the ellipse eccentricity is varying longitudinally on the missile. The cross flow velocity on a triform fin section is also studied
An experimental wind-tunnel investigation was conducted at Mach numbers from 1.60 to 3.50 to obtain ...
Longitudinal aerodynamic characteristics of a configuration consisting of an elliptical body with an...
An experimental investigation was conducted to provide a systematic set of lateral-directional stabi...
Slender body methods have been applied to some specialized problems associated with missile configur...
Tabulated body surface pressure data for two monoplane-wing missile configurations are presented and...
A general procedure for computing the region of influence of a maneuvering vehicle is described. Bas...
A computer program developed for determining the subsonic pressure, force, and moment coefficients f...
Experimental aerodynamic characteristics of a low-drag missile concept with a body of circular cross...
Computer programs are presented which are capable of calculating detailed aerodynamic loadings and p...
Three missile body shapes tested at Mach numbers of 1.50, 2.16, and 2.86 with angles of attack up to...
The tests were performed at a Mach number of 2.50 and at angles of attack from about -4 deg to 32 de...
An investigation was conducted of a monoplanar maneuverable missile concept having a nose forebody w...
An experimental investigation was conducted to measure the static aerodynamic characteristics for tw...
This proposal describes the first phase of the work comtemplated for the Missile Design Manual . The...
One geometry currently under consideration for the Aeroassist Flight Experiment (AFE) vehicle is com...
An experimental wind-tunnel investigation was conducted at Mach numbers from 1.60 to 3.50 to obtain ...
Longitudinal aerodynamic characteristics of a configuration consisting of an elliptical body with an...
An experimental investigation was conducted to provide a systematic set of lateral-directional stabi...
Slender body methods have been applied to some specialized problems associated with missile configur...
Tabulated body surface pressure data for two monoplane-wing missile configurations are presented and...
A general procedure for computing the region of influence of a maneuvering vehicle is described. Bas...
A computer program developed for determining the subsonic pressure, force, and moment coefficients f...
Experimental aerodynamic characteristics of a low-drag missile concept with a body of circular cross...
Computer programs are presented which are capable of calculating detailed aerodynamic loadings and p...
Three missile body shapes tested at Mach numbers of 1.50, 2.16, and 2.86 with angles of attack up to...
The tests were performed at a Mach number of 2.50 and at angles of attack from about -4 deg to 32 de...
An investigation was conducted of a monoplanar maneuverable missile concept having a nose forebody w...
An experimental investigation was conducted to measure the static aerodynamic characteristics for tw...
This proposal describes the first phase of the work comtemplated for the Missile Design Manual . The...
One geometry currently under consideration for the Aeroassist Flight Experiment (AFE) vehicle is com...
An experimental wind-tunnel investigation was conducted at Mach numbers from 1.60 to 3.50 to obtain ...
Longitudinal aerodynamic characteristics of a configuration consisting of an elliptical body with an...
An experimental investigation was conducted to provide a systematic set of lateral-directional stabi...