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A computational system for aerodynamic design and analysis of supersonic aircraft. Part 3: Computer program description

W. D. Middleton, J. L. Lundry, Roger G. Coleman

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Abstract

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.The description of the design and analysis system is broken into three parts, covered in three separate documents: Part 1 -General Description and Theoretical Development Part 2-User's Manual Part 3-Computer Program Description This part contains schematics of the program structure and describes the individual overlays and subroutines.These three documents supersede NASA contractor reports CR-2520, CR-2521, and CR-2522, which described an earlier version of the system.

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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.The description of the design and analysis system is broken into three parts, covered in three separate documents: Part 1 -General Description and Theoretical Development Part 2-User's Manual Part 3-Computer Program Description This part contains schematics of the program structure and describes the individual overlays and subroutines.These three documents supersede NASA contractor reports CR-2520, CR-2521, and CR-2522, which described an earlier version of the system.

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Available abstract

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.The description of the design and analysis system is broken into three parts, covered in three separate documents: Part 1 -General Description and Theoretical Development Part 2-User's Manual Part 3-Computer Program Description This part contains schematics of the program structure and describes the individual overlays and subroutines.These three documents supersede NASA contractor reports CR-2520, CR-2521, and CR-2522, which described an earlier version of the system.

Key concepts: Supersonic speed, Aerodynamics, Computer science, Aerospace engineering, Aeronautics, Computer program, Engineering, Systems engineering

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