Add to ORKGAn introduction to the problem of determining the fundamental limitations on the performance possibilities of rocket-powered aircraft is presented. Previous material on the subject is reviewed and given in condensed form along with supplementary analyses. Some of the problems discussed are: 1) limiting velocity of a rocket projectile; 2) limiting velocity of a rocket jet; 3) jet efficiency; 4) nozzle characteristics; 5) maximum attainable altitudes; 6) ranges. Formulas are presented relating the performance of a rocket-powered aircraft to basic weight and nozzle dimensional parameters. The use of these formulas is illustrated by their application to the special case of a nonlifting rocket projectile
Maximum range trajectories for rocket propelled lunar flying vehicles in uniform gravitational fiel
A rocket engine with an exhaust-nozzle area ratio of 25 was operated at a constant chamber pressure ...
Long-range hypervelocity vehicles are studied in terms of their motion in powered flight, and their ...
An introduction to the problem of determining the fundamental limitations on the performance possibi...
Although the Chinese are credited with the use of gunpowder rockets as early as several centuries B....
Calculating rocket vertical flight performance using Newtons law to compute acceleratio
NOTE: Text of symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in ...
The effect on performance of variations in power plant, aircraft, and rocket parameters was calculat...
Includes bibliographical references (pages 62-65)This project analyzes the performance of the\ud ram...
Newtons second and third laws for basic concepts of thrust, and fundamental design criteria for rock...
Summary of configurations, major systems, and performance equations for launch vehicle
Use of high-performance aircraft as first-stage booster for air-launching solid fuel rocket - operat...
A new method of power plant selection for vertical flight is proposed. It can be used to determine w...
Solid propellant rocket systems design and combustion efficiency and burning rate of solid propellan...
When considering the problems of basic research in rocket and jet propulsion, it is profitable to ke...
Maximum range trajectories for rocket propelled lunar flying vehicles in uniform gravitational fiel
A rocket engine with an exhaust-nozzle area ratio of 25 was operated at a constant chamber pressure ...
Long-range hypervelocity vehicles are studied in terms of their motion in powered flight, and their ...
An introduction to the problem of determining the fundamental limitations on the performance possibi...
Although the Chinese are credited with the use of gunpowder rockets as early as several centuries B....
Calculating rocket vertical flight performance using Newtons law to compute acceleratio
NOTE: Text of symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in ...
The effect on performance of variations in power plant, aircraft, and rocket parameters was calculat...
Includes bibliographical references (pages 62-65)This project analyzes the performance of the\ud ram...
Newtons second and third laws for basic concepts of thrust, and fundamental design criteria for rock...
Summary of configurations, major systems, and performance equations for launch vehicle
Use of high-performance aircraft as first-stage booster for air-launching solid fuel rocket - operat...
A new method of power plant selection for vertical flight is proposed. It can be used to determine w...
Solid propellant rocket systems design and combustion efficiency and burning rate of solid propellan...
When considering the problems of basic research in rocket and jet propulsion, it is profitable to ke...
Maximum range trajectories for rocket propelled lunar flying vehicles in uniform gravitational fiel
A rocket engine with an exhaust-nozzle area ratio of 25 was operated at a constant chamber pressure ...
Long-range hypervelocity vehicles are studied in terms of their motion in powered flight, and their ...