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Id
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DLNET-12-06-2002-0110
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Title
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Author(s)
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Robert D. Quinn,Leslie Gong
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E-mail(s)
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n/a,n/a
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Department
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Dryden Flight Research Center,Dryden Flight Research Center
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Organization
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NASA,NASA
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Description
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This report describes a method that can calculate transient aerodynamic heating and transient surface temperatures at supersonic and hypersonic speeds. This method can rapidly calculate temperature and heating rate time-histories for complete flight trajectories. Semi-empirical theories are used to calculate laminar and turbulent heat transfer coefficients and a procedure for estimating boundary-layer transition is included. Results from this method are compared with flight data from the X-15 research vehicle, YF-12 airplane, and the Space Shuttle Orbiter. These comparisons show that the calculated values are in good agreement with the measured flight data.
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Keywords
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Aerodynamic heating; Boundary layer; Flight measurements; Flow hypersonic; Flow inviscid, Boundary Layer, Flight Measurements, Flow Hypersonic, Flow Inviscid
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Classification
| Aerospace Aeronautical Engineering/ Aerodynamics/ Computational Aerodynamics/Fluid Dynamics |
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Date
of Creation
| 2000-12-01 |
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Resource URL
| Not Available |
| Copyright Information | Resource has NO copyright restrictions; the contributor(s) agree to its free and unrestricted use for standard educational purposes. |
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Format
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Portable Document Format (.pdf)
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Size
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344 KB
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Requirements
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Application Program: Adobe Acrobat Reader
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Interactivity
Type
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EXPOSITIVE: Information flows from resource to learner only
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Resource
Type
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Narrative Texts, Abstracts
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Interactivity
Level
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MEDIUM: Some interaction/input required from learner
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Intended
Audience
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Learners
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Context
of Use
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Professional Formations, Vocational Training, Continuous Formations
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Learning
Duration
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3 hours
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This resource has
the following component(s):
H-2427.pdf
For more information on the meaning of the metadata presented here, please visit the DLNET website. Thank you for using DLNET learning object.