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GAS TURBINE ENGINE INLET FLOW DISTORTION GUIDELINES
- Aerospace Standard
Downloadable datasets availableAnnotation ability available
The turbine-engine inlet flow distortion methodology addressed in this document applies only to the effects of inlet total-pressure distortion. Practices employed to quantify these effects are developing and therefore, periodic updates are anticipated. The effects of other forms of distortion on flow stability and performance and of any distortion on aeroelastic stability are not addressed.
The guidelines can be used as necessary to create a development method to minimize the risk of inlet/engine compatibility problems. The degree to which guidelines for descriptor use, assessment techniques, and testing outlined in this document are applied to a specific program should be consistent with the expected severity of the compatibility problem.
|Aerospace Standard||Gas Turbine Engine Inlet Flow Distortion Guidelines|
|Technical Paper||Designing Based on Thermal Loads|
|Technical Paper||Assessment of Technology Readiness Level of a Carbon Dioxide Reduction Assembly (CRA) for Use on International Space Station|
Data Sets - Support Documents
|Table I||Data Scaling Guidelines. Strouhal Number Constant (Same Reynolds Number and Mach Number)|
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