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Parametric study on laminar flow for finite wings at supersonic speeds
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Garcia, Joseph Avila |
| Copyright Year | 1994 |
| Description | Laminar flow control has been identified as a key element in the development of the next generation of High Speed Transports. Extending the amount of laminar flow over an aircraft will increase range, payload, and altitude capabilities as well as lower fuel requirements, skin temperature, and therefore the overall cost. A parametric study to predict the extent of laminar flow for finite wings at supersonic speeds was conducted using a computational fluid dynamics (CFD) code coupled with a boundary layer stability code. The parameters investigated in this study were Reynolds number, angle of attack, and sweep. The results showed that an increase in angle of attack for specific Reynolds numbers can actually delay transition. Therefore, higher lift capability, caused by the increased angle of attack, as well as a reduction in viscous drag, due to the delay in transition, can be expected simultaneously. This results in larger payload and range. |
| File Size | 3833120 |
| Page Count | 108 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19950011686 |
| Archival Resource Key | ark:/13960/t43r5sm6s |
| Language | English |
| Publisher Date | 1994-12-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Wings Laminar Boundary Layer Supersonic Aircraft Supersonic Speed Drag Reduction Computational Fluid Dynamics Laminar Flow Reynolds Number Boundary Layer Stability Angle of Attack Boundary Layer Control Boundary Layer Equations Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
