Add to ORKGStrain gages, nitrocellulose effects, and mathematical models for hypervelocity launch tubes with propellant linin
Effects of target strength on cratering process caused by impact of hypervelocity projectile
Performance analysis of a gas-driven shock tube shows that transonic airfoil flows with chord Reynol...
Results of an experimental investigation of expansion tube flow characteristics performed with heliu...
Feasibility of explosive lining in launch tube for hypervelocity projectile acceleratio
A four month feasibility study of a hypersonic real-gas free flight test facility for NASA Langley R...
Optimization of the propellant reorientation process can provide increased payload capability and ex...
Addition of kinetic energy to supersonic exhaust of shock tunnel by reversing flow direction with hi...
A preliminary theoretical study was conducted of a new technique for producing high-enthalpy gas flo...
Space storable surface tension propellant acquisition system for Mars and Grand Tour mission
Reactivity and expansion characteristics of Aerozine-50 and nitrogen tetroxide from vacuum chamber t...
Critical appraisal of design, development, and operation of UTIAS implosion-driven shock tubes and h...
Described are the modifications currently under way to the Langley 8-Foot High Temperature Tunnel to...
Shock tube instrumentation methods for convective heat transfer study and radiative properties of hi...
The feasibility of potential reusable thrust chamber concepts is studied. Propellant condidates were...
Space storable propellant acquisition, pressurization, and tankage propulsion subsystems for Mars an...
Effects of target strength on cratering process caused by impact of hypervelocity projectile
Performance analysis of a gas-driven shock tube shows that transonic airfoil flows with chord Reynol...
Results of an experimental investigation of expansion tube flow characteristics performed with heliu...
Feasibility of explosive lining in launch tube for hypervelocity projectile acceleratio
A four month feasibility study of a hypersonic real-gas free flight test facility for NASA Langley R...
Optimization of the propellant reorientation process can provide increased payload capability and ex...
Addition of kinetic energy to supersonic exhaust of shock tunnel by reversing flow direction with hi...
A preliminary theoretical study was conducted of a new technique for producing high-enthalpy gas flo...
Space storable surface tension propellant acquisition system for Mars and Grand Tour mission
Reactivity and expansion characteristics of Aerozine-50 and nitrogen tetroxide from vacuum chamber t...
Critical appraisal of design, development, and operation of UTIAS implosion-driven shock tubes and h...
Described are the modifications currently under way to the Langley 8-Foot High Temperature Tunnel to...
Shock tube instrumentation methods for convective heat transfer study and radiative properties of hi...
The feasibility of potential reusable thrust chamber concepts is studied. Propellant condidates were...
Space storable propellant acquisition, pressurization, and tankage propulsion subsystems for Mars an...
Effects of target strength on cratering process caused by impact of hypervelocity projectile
Performance analysis of a gas-driven shock tube shows that transonic airfoil flows with chord Reynol...
Results of an experimental investigation of expansion tube flow characteristics performed with heliu...