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Sonic-box method employing local mach number for oscillating wings with thickness
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ruo, S. Y. |
| Copyright Year | 1978 |
| Description | A computer program was developed to account approximately for the effects of finite wing thickness in the transonic potential flow over an oscillating wing of finite span. The program is based on the original sonic-box program for planar wing which was previously extended to include the effects of the swept trailing edge and the thickness of the wing. Account for the nonuniform flow caused by finite thickness is made by application of the local linearization concept. The thickness effect, expressed in terms of the local Mach number, is included in the basic solution to replace the coordinate transformation method used in the earlier work. Calculations were made for a delta wing and a rectangular wing performing plunge and pitch oscillations, and the results were compared with those obtained from other methods. An input quide and a complete listing of the computer code are presented. |
| File Size | 2233708 |
| Page Count | 73 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790002828 |
| Archival Resource Key | ark:/13960/t2p60cf6w |
| Language | English |
| Publisher Date | 1978-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Thickness Transonic Flow Airfoil Profiles Wing Oscillations Surfaces Aerodynamic Characteristics Computer Programs Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
