The Apollo program offered the first opportunity to obtain aerothermodynamic measurements at superorbital velocities on full-scale spacecraft. Four unmanned flight tests were conducted to qualify the Apollo command module heat shield. Aerothermodynamic measurements were made, and data are presented to illustrate the comparison of the flight data with the ground-test results and theoretical predictions
Launch vehicle flight tests of effects of Apollo heat shield irregularities on ablative material per...
Transient heat transfer and thermodynamic behavior analysis for Apollo service module propulsion sys...
The prelaunch, lift-off, and midboost conditions that are important to the design of spacecraft are ...
Portions of the combined Apollo spacecraft (the command and service module and the lunar module) are...
The evolution of the thermal design of the Apollo lunar surface experiments package central station ...
Heat transfer rate and pressure measurements obtained on Apollo command module during atmospheric en...
Protuberances, cavities, and angle of attack effect on wind tunnel pressure and heat transfer distri...
Impact water pressures, accelerations, and landing dynamics of scale model Apollo command module wit...
The evolution of the thermal design of the Apollo lunar surface experiments package central station ...
The aerodynamic and aerothermal heating at the leeward surfaces of the Apollo capsule flying high an...
An experimental wind tunnel program is being conducted in support of a NASA wide effort to develop a...
Apollo/Saturn I unmanned space flight to test command module ablative heat shiel
The method and data for determining the accelerations on the heat flow and convection demonstration ...
The problems encountered and the experience gained in the entry mission plans, flight software, traj...
Reynolds and Mach numbers simulation of Apollo and Gemini reentry compared with flight dat
Launch vehicle flight tests of effects of Apollo heat shield irregularities on ablative material per...
Transient heat transfer and thermodynamic behavior analysis for Apollo service module propulsion sys...
The prelaunch, lift-off, and midboost conditions that are important to the design of spacecraft are ...
Portions of the combined Apollo spacecraft (the command and service module and the lunar module) are...
The evolution of the thermal design of the Apollo lunar surface experiments package central station ...
Heat transfer rate and pressure measurements obtained on Apollo command module during atmospheric en...
Protuberances, cavities, and angle of attack effect on wind tunnel pressure and heat transfer distri...
Impact water pressures, accelerations, and landing dynamics of scale model Apollo command module wit...
The evolution of the thermal design of the Apollo lunar surface experiments package central station ...
The aerodynamic and aerothermal heating at the leeward surfaces of the Apollo capsule flying high an...
An experimental wind tunnel program is being conducted in support of a NASA wide effort to develop a...
Apollo/Saturn I unmanned space flight to test command module ablative heat shiel
The method and data for determining the accelerations on the heat flow and convection demonstration ...
The problems encountered and the experience gained in the entry mission plans, flight software, traj...
Reynolds and Mach numbers simulation of Apollo and Gemini reentry compared with flight dat
Launch vehicle flight tests of effects of Apollo heat shield irregularities on ablative material per...
Transient heat transfer and thermodynamic behavior analysis for Apollo service module propulsion sys...
The prelaunch, lift-off, and midboost conditions that are important to the design of spacecraft are ...