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Study of the supersonic propeller
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1953 |
| Description | In this paper a propeller having all sections operating at supersonic speeds is designated a supersonic propeller regardless of flight speed. Analyses assume subsonic flight speeds but very high rotational speeds. A very elementary analysis of the efficiency of a jet-propeller system is presented. A propeller analysis based on conventional vortex blade element theory is presented and reduced to a single point method which leads to an expression for optimum advance ratio in terms of hub-tip diameter ratio and airfoil fineness ratio. An expression for propeller efficiency in terms of advance ratio, hub-tip diameter ratio, and airfoil thickness ratio is also presented. Use is made of theoretical airfoil characteristics at supersonic speeds. A study of blade section interference, blade shock and expansion fields, at supersonic section speeds is presented. An example taken indicates that an efficiency of seventy percent can be obtained with a propeller having a tip Mach number of 2.3. |
| File Size | 5572620 |
| Page Count | 24 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930093875 |
| Archival Resource Key | ark:/13960/t33249376 |
| Language | English |
| Publisher Date | 1953-03-01 |
| Access Restriction | Open |
| Subject Keyword | Propellers, Supersonic Theories - Vortex - Propellers Propeller Slipstream Engines, Turbo-propeller Mach Number Effects - Propellers Propellers - Design Variables Propeller Theory Interference - Propeller Blades 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 |
