Equations and Charts for the Evaluation of the Hypersonic Aerodynamic Characteristics of Lifting Configurations by the Newtonian Theory
Report Number: AEDC TDR 64-25
Author(s): Clark, E. L., Trimmer, L. L.
Corporate Author(s): ARO, Inc.
Laboratory: Arnold Engineering Development Center
Date of Publication: 1964-03
Pages: 93
Contract: AF 40(600)-1000
DoD Project: None Given
Identifier: AD0431848
Abstract:
The pressure distribution predicted by the modified Newtonian theory is used to develop equations for the aerodynamic forces, moments, and stability derivatives for components of hypersonic lifting configurations. In conjunction with the equations, a set of charts is presented to enable simple determination of the aerodynamic characteristics of swept cylinders, swept wedges, spherical segments, and cone frustums at zero sideslip and angles of attack from 0 to 180 degrees. This method allows evaluation of most delta wing-body combinations without the need for numerical or graphical integration. As an example of the procedure, the theoretical characteristics of a blunt 75-degree swept delta wing are calculated and compared with experimental results.
Provenance: IIT
Author(s): Clark, E. L., Trimmer, L. L.
Corporate Author(s): ARO, Inc.
Laboratory: Arnold Engineering Development Center
Date of Publication: 1964-03
Pages: 93
Contract: AF 40(600)-1000
DoD Project: None Given
Identifier: AD0431848
Abstract:
The pressure distribution predicted by the modified Newtonian theory is used to develop equations for the aerodynamic forces, moments, and stability derivatives for components of hypersonic lifting configurations. In conjunction with the equations, a set of charts is presented to enable simple determination of the aerodynamic characteristics of swept cylinders, swept wedges, spherical segments, and cone frustums at zero sideslip and angles of attack from 0 to 180 degrees. This method allows evaluation of most delta wing-body combinations without the need for numerical or graphical integration. As an example of the procedure, the theoretical characteristics of a blunt 75-degree swept delta wing are calculated and compared with experimental results.
Provenance: IIT