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Aerodynamic effects of nearly uniform slipstreams on thin wings in the transonic regime
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Rizk, M. H. |
| Copyright Year | 1980 |
| Description | A simplified model is used to describe the interaction between a propeller slipstream and a wing in the transonic regime. The undisturbed slipstream boundary is assumed to coincide with an infinite circular cylinder. The undisturbed slipstream velocity is rotational and is a function of the radius only. In general, the velocity perturbation caused by introducing a wing into the slipstream is also rotational. By making small disturbance assumptions, however, the perturbation velocity becomes nearly potential, and an approximation for the flow is obtained by solving a potential equation. |
| File Size | 3378617 |
| Page Count | 61 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810009504 |
| Archival Resource Key | ark:/13960/t8ff8kn9f |
| Language | English |
| Publisher Date | 1980-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Turboprop Aircraft Transonic Flow Iterative Solution Finite Difference Theory Wing Planforms Slipstreams Pressure Distribution Thin Wings Aerodynamic Characteristics Equations Circular Cylinders Potential Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
