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Inlet/Engine Compatibility - From Model to Full Scale Development
- Aerospace Standard
- AIR5687A
- Stabilized
Downloadable datasets available
Annotation ability available
Sector:
Issuing Committee:
Language:
English
Scope
This document reviews the state of the art for data scaling issues associated with air induction system development for turbine-engine-powered aircraft. In particular, the document addresses issues with obtaining high quality aerodynamic data when testing inlets. These data are used in performance and inlet-engine compatibility analyses. Examples of such data are: inlet recovery, inlet turbulence, and steady-state and dynamic total-pressure inlet distortion indices. Achieving full-scale inlet/engine compatibility requires a deep understanding of three areas: 1) geometric scaling fidelity (referred to here as just “scaling”), 2) impact of Reynolds number, and 3) ground and flight-test techniques (including relevant environment simulation, data acquisition, and data reduction practices). The Model-to-Full Scale Subcommittee of the S-16 Turbine Engine Inlet Flow Distortion Committee has examined archives and has obtained recollections of experts regarding air induction system development experience to produce this document.
Rationale
The intent of this document is to capture the experience and lessons learned since approximately 1967 necessary to ensure that model-scale inlet total-pressure recovery and distortion data faithfully represent the corresponding full-scale inlet recovery and distortion characteristics.
This document contains information that is fundamental to the discipline of inlet-engine compatibility and is expected to remain stable for the foreseeable future.
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| Aerospace Standard | Distortion Synthesis/Estimation Techniques |
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Topic
Data Sets - Support Documents
| Title | Description | Download |
|---|---|---|
| Unnamed Dataset 1 | ||
| TABLE 1 | EARLY AIRCRAFT PROGRAMS OFFERING INSIGHT INTO THE EVOLUTION OF INLET/AIRFRAME INTEGRATION TECHNOLOGY | |
| TABLE 2 | AIRCRAFT PROGRAMS OFFERING WIND TUNNEL TO FLIGHT CORRELATIONS OF INLET RECOVERY AND DYNAMIC TOTAL-PRESSURE DISTORTION | |
| TABLE 3 | F-15 TEST CONDITIONS | |
| TABLE 4 | TOLERANCES FOR TRIM AND MANEUVER FLIGHT CONDITIONS |
Issuing Committee
S-16 Turbine Engine Inlet Flow Distortion Committee
Scope: Committee S-16 develops uniform procedures for adoption by industry. These procedures will permit representation of inletdistortion and evaluation of its effect on propulsion systems' stability and performance.
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