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Three-dimensional transonic flow theory applied to slender wings and bodies
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1957 |
| Description | The present paper re-examines the derivation of the integral equations for transonic flow around slender wings and bodies of revolution, giving special attention to conditions resulting from the presence of shock waves and to the reduction of the relations to the special forms necessary for the discussion of sonic flow, that is, flow at free-stream Mach number 1. |
| File Size | 30588331 |
| Page Count | 35 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930092309 |
| Archival Resource Key | ark:/13960/t6m08v14s |
| 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 |