Add to ORKGForce Measurements On Four Nose Configurations With Cylindrical After body Were Performed In 0.3m Wind Tunnel In The Mach Number Range Of 0.5 To 0.8 And Angle Of Incidence -4 To 14°.From Analysis Of Aerodynamic Data, It Was Observed That The Bulbous Nose Configuration Was The Optimum Configuration With Drag Penalty.\ud \u
A wind tunnel investigation has been conducted at Mach numbers from 0.9 to 1.4 to determine the net-...
An experimental investigation in the Langley Gas Dynamics Laboratory has been made of the flow separ...
High angle aerodynamic characteristics produced by nose cone of revolution in wind tunnel at superso...
A new nose shape that was determined using the penetration mechanics to have the least penetration d...
For a body of revolution with afterbody side strakes, an experimental investigation was conducted in...
The subject of this paper is the drag of the nose section of bodies of revolution at zero angle of a...
Values of total drag coefficient were measured for four round-nosed bodies of revolution in free fli...
Values of total-drag coefficient were measured for two fin-stabilized, blunt-nose bodies of revoluti...
Experimental drag measurements at zero angle of attack for various theoretical minimum drag nose sha...
An investigation has been conducted in 1 ' x 1 ' trisonic tunnel of National Aeronautical Laboratory...
The tests were performed at a Mach number of 2.50 and at angles of attack from about -4 deg to 32 de...
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in...
An experimental investigation to determine the aerodynamic characteristics of a slender body of revo...
An experimental investigation was conducted in the AEDC 16-foot Transonic Wind Tunnel (16T) to deter...
Pressure distributions and forces for a series of four bodies of revolution having nose-fineness rat...
A wind tunnel investigation has been conducted at Mach numbers from 0.9 to 1.4 to determine the net-...
An experimental investigation in the Langley Gas Dynamics Laboratory has been made of the flow separ...
High angle aerodynamic characteristics produced by nose cone of revolution in wind tunnel at superso...
A new nose shape that was determined using the penetration mechanics to have the least penetration d...
For a body of revolution with afterbody side strakes, an experimental investigation was conducted in...
The subject of this paper is the drag of the nose section of bodies of revolution at zero angle of a...
Values of total drag coefficient were measured for four round-nosed bodies of revolution in free fli...
Values of total-drag coefficient were measured for two fin-stabilized, blunt-nose bodies of revoluti...
Experimental drag measurements at zero angle of attack for various theoretical minimum drag nose sha...
An investigation has been conducted in 1 ' x 1 ' trisonic tunnel of National Aeronautical Laboratory...
The tests were performed at a Mach number of 2.50 and at angles of attack from about -4 deg to 32 de...
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in...
An experimental investigation to determine the aerodynamic characteristics of a slender body of revo...
An experimental investigation was conducted in the AEDC 16-foot Transonic Wind Tunnel (16T) to deter...
Pressure distributions and forces for a series of four bodies of revolution having nose-fineness rat...
A wind tunnel investigation has been conducted at Mach numbers from 0.9 to 1.4 to determine the net-...
An experimental investigation in the Langley Gas Dynamics Laboratory has been made of the flow separ...
High angle aerodynamic characteristics produced by nose cone of revolution in wind tunnel at superso...