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An analysis of the effects of aeroelasticity on static longitudinal stability and control of a swept-wing airplane
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1957 |
| Description | A theoretical analysis has been made of the effects of aeroelasticity on the static longitudinal stability and elevator angle required for balance of an airplane. The analysis is based on the familiar stability equation expressing the contribution of wing and tail to longitudinal stability. Effects of wing, tail, and fuselage flexibility are considered. Calculated effects are shown for a swept-wing bomber of relatively high flexibility. |
| File Size | 1334650 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930092293 |
| Archival Resource Key | ark:/13960/t3fz20v5p |
| Language | English |
| Publisher Date | 1957-01-01 |
| Access Restriction | Open |
| Subject Keyword | Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |