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Subsonic flow investigations on a cranked wing designed for high maneuverability
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Rao, D. M. |
| Copyright Year | 1986 |
| Description | The characteristic pitching moment nonlinearity of cranked wings limits their usable lift coefficient well below C sub L max. The potential of several aerodynamic devices, viz., fences, pylon vortex generators (PVG), mid-span strakes and cavity flaps, in delaying the pitch up onset on a 70/50 deg cranked wing was explored in low speed tunnel tests. Upper surface pressure measurements and low visualizations were conducted on a semi-span wing model to observe the vortex flow development with increasing angle of attack, and then to assess the effectiveness of the devices in controlling the collapse of vortex lift over the wing panel outboard of the crank. Force tests on a full span wing and body model were also conducted to assess the fence and PVG in improving the usable C sub L. |
| File Size | 5731119 |
| Page Count | 45 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19860010890 |
| Archival Resource Key | ark:/13960/t3421vh1g |
| Language | English |
| Publisher Date | 1986-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Vortex Alleviation Pressure Drag Pitching Moments Maneuverability Longitudinal Control Swept Wings Vortices Subsonic Flow Wind Tunnel Tests Flow Visualization Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
