Unsteady Aerodynamics for Advanced Configurations: Part V - Unsteady Potential Flow Around Slender Bodies at Angles of Attack

Item

Title
Unsteady Aerodynamics for Advanced Configurations: Part V - Unsteady Potential Flow Around Slender Bodies at Angles of Attack
Date
1965
Index Abstract
Coming Soon
Photo Quality
Not Needed
Report Number
FDL TDR 64-152 Part 5
Creator
Li, T. C.
Corporate Author
North American Aviation, Incorporated
Laboratory
Air Force Flight Dynamics Laboratory
Extent
52
Identifier
AD0619397
Access Rights
Notice(s)
Distribution Classification
1
Contract
AF 33(657)-10399
DoD Project
1370
DoD Task
137003
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Abstract
In the portion of the study covered in this report, linearized theory is developed for potential flow around a slender body at not too large angles of attack. The solution is obtained by 'definitizing' the flow equation and rigorously satisfying the boundary conditions. This approach is completely different from conventional methods in that it constitutes a process of obtaining an analytic solution to the problem of potential flow by a 'march from the body' toward infinity. The extension of this new theory to the nonlinear case is immediate. Having shown it is possible to not restrict the Mach number, it is expected that the new theory should be applicable to the cases of subsonic, transonic and supersonic speeds as well.
Report Availability
Full text available
Date Issued
1965-05
Provenance
AFRL/VACA
Type
report
Format
1 online resource
Media
FDLTDR64-152part05.pdf

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