32 research outputs found
A numerical solution for the minimum induced drag, and the corresponding loading, of nonplanar wings Final report
Numerical solution for minimum induced drag, and associated loading, of nonplanar wing
A computational system for aerodynamic design and analysis of supersonic aircraft. Part 1: General description and theoretical development
An integrated system of computer programs was developed for the design and analysis of supersonic configurations. The system uses linearized theory methods for the calculation of surface pressures and supersonic area rule concepts in combination with linearized theory for calculation of aerodynamic force coefficients. Interactive graphics are optional at the user's request. Schematics of the program structure and the individual overlays and subroutines are described
A system for aerodynamic design and analysis of supersonic aircraft. Part 4: Test cases
An integrated system of computer programs was developed for the design and analysis of supersonic configurations. The system uses linearized theory methods for the calculation of surface pressures and supersonic area rule concepts in combination with linearized theory for calculation of aerodynamic force coefficients. Interactive graphics are optional at the user's request. Representative test cases and associated program output are presented
A system for aerodynamic design and analysis of supersonic aircraft. Part 1: General description and theoretical development
An integrated system of computer programs was developed for the design and analysis of supersonic configurations. The system uses linearized theory methods for the calculation of surface pressures and supersonic area rule concepts in combination with linearized theory for calculation of aerodynamic force coefficients
Aerodynamic design and analysis system for supersonic aircraft. Part 1: General description and theoretical development
An integrated system of computer programs has been developed for the design and analysis of supersonic configurations. The system uses linearized theory methods for the calculation of surface pressures and supersonic area rule concepts in combination with linearized theory for calculation of aerodynamic force coefficients. Interactive graphics are optional at the user's request. This part presents a general description of the system and describes the theoretical methods used
A system for aerodynamic design and analysis of supersonic aircraft. Part 3: Computer program description
The computer program documentation for the design and analysis of supersonic configurations is presented. Schematics and block diagrams of the major program structure, together with subroutine descriptions for each module are included
A computational system for aerodynamic design and analysis of supersonic aircraft. Part 2: User's manual
An integrated system of computer programs was developed for the design and analysis of supersonic configurations. The system uses linearized theory methods for the calculation of surface pressures and supersonic area rule concepts in combination with linearized theory for calculation of aerodynamic force coefficients. Interactive graphics are optional at the user's request. This user's manual contains a description of the system, an explanation of its usage, the input definition, and example output
Aerodynamic design and analysis system for supersonic aircraft. Part 2: User's manual
An integrated system of computer programs for supersonic configurations is described. An explanation of system usage, the input definitions, and example output are included. For Part 1, see N75-18185; for Part 3, see N75-18186
A computational system for aerodynamic design and analysis of supersonic aircraft. Part 3: Computer program description
For abstract, see Vol. 1