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A Method for Evaluating the Effects of Drag and Inlet Pressure Recovery on Propulsion -system Performance
| Content Provider | Semantic Scholar |
|---|---|
| Author | Kremzier, Emil J. |
| Copyright Year | 1954 |
| Abstract | SUMMARY A method of evaluating the ratio of aircraft thrust minus drag to ideal thrust for any inlet ~ressure recovery is presented for airplanes with air-breathing propulsion systems. The quantities required for this evaluation include flight Mach number and altitude, engine totalpressure ratio and total-temperature ratio, engine air-flow requirements, and airplane drag. Variation of the ratio of incremental changes in inlet pressure recovery to incremental changes in drag coefficient required to maintain a given level of airplane or propulsion-system thrust minus drag is presented. Three types of typical air-breathing engine having equal air-flow capacities are compared at given operating points. Application of the method to the determination of inlet mass-flow ratio for maximum thrust minus drag is also included • INTROOOCTION The air-induction system of an aircraft with an air-breathing engine should supply the prescribed air flow to the engine at high pressure recovery with as little external drag as possible. It is often possible to increase the internal thrust of the propulsion system through inlet design modifications that increase the operating pressure recovery of the inlet. |
| File Format | PDF HTM / HTML |
| Alternate Webpage(s) | https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19930084001.pdf |
| Alternate Webpage(s) | https://digital.library.unt.edu/ark:/67531/metadc57237/m2/1/high_res_d/19930084001.pdf |
| Language | English |
| Access Restriction | Open |
| Content Type | Text |
| Resource Type | Article |
