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Unsteady aerodynamic analysis of space shuttle vehicles. part 1: summary report
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ericsson, L. E. Reding, J. P. |
| Copyright Year | 1973 |
| Description | An analysis of the unsteady aerodynamics of space shuttle vehicles was performed. The results show that slender wing theory can be modified to give the potential flow static and dynamic characteristics over a large Mach number range from M = 0 to M 1. A semi-empirical analytic approximation is derived for the loads induced by the leading edge vortex; and it is shown that the developed analytic technique gives good prediction of experimentally determined steady and unsteady delta wing aerodynamics, including the effects of leading edge roundness. At supersonic speeds, attached leading edge flow is established and shock-induced flow separation effects become of concern. Analysis of experimental results for a variety of boost configurations led to a definition of the main features of the flow interference effects between orbiter (delta wing) and booster. The effects of control deflection on the unsteady aerodynamics of the delta-wing orbiter were also evaluated. |
| File Size | 3988931 |
| Page Count | 80 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730024030 |
| Archival Resource Key | ark:/13960/t6p02z01g |
| Language | English |
| Publisher Date | 1973-08-01 |
| Access Restriction | Open |
| Subject Keyword | Space Vehicles Slender Wings Aerodynamic Configurations Space Shuttles Delta Wings Unsteady Aerodynamics Flow Characteristics Aerodynamics Unsteady Flow Separated Flow Leading Edges Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
