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Supersonic pressure measurements and comparison of theory to experiment for an arrow-wing configuration
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Manro, M. E. |
| Copyright Year | 1976 |
| Description | A wind tunnel test of an arrow-wing-body configuration consisting of flat and twisted wings, as well as leading- and trailing-edge control surface deflections, was conducted at Mach numbers from 1.54 to 2.50 to provide an experimental pressure data base for comparison with theoretical methods. Theory-to-experiment comparisons of detailed pressure distributions were made using a state-of-the-art inviscid flow, constant-pressure-panel method. Emphasis was on conditions under which this theory is valid for both flat and twisted wings. |
| File Size | 58387034 |
| Page Count | 701 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770010057 |
| Archival Resource Key | ark:/13960/t6547h38f |
| Language | English |
| Publisher Date | 1976-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Supersonic Flow Arrow Wings Body-wing Configurations Control Surfaces Wind Tunnel Tests Pressure Distribution Wing Span Aircraft Design Wing Loading Aerodynamic Loads Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
