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Subsonic flow over thin oblique airfoils at zero lift
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1948 |
| Description | A previous report gave calculations for the pressure distribution over thin oblique airfoils at supersonic speed. The present report extends the calculations to subsonic speeds. It is found that the flows again can be obtained by the superposition of elementary conical flow fields. In the case of the swept-back wing the pressure distributions remain qualitatively similar at subsonic and supersonic speeds. Thus a distribution similar to the Ackeret type of distribution appears on the root sections of the swept-back wing at Mach=0. The resulting positive pressure drag on the root section is balanced by negative drags on outboard sections. |
| File Size | 556384 |
| Page Count | 7 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930091969 |
| Archival Resource Key | ark:/13960/t3809f42n |
| Language | English |
| Publisher Date | 1948-01-01 |
| Access Restriction | Open |
| Subject Keyword | Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
