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Effect of tail size reductions on longitudinal aerodynamic characteristics of a three surface f-15 model with nonaxisymmetric nozzles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Frassinelli, Mark C. Carson Jr., George T. |
| Copyright Year | 1990 |
| Description | An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the effects of horizontal and vertical tail size reductions on the longitudinal aerodynamic characteristics of a modified F-15 model with canards and 2-D convergent-divergent nozzles. Quantifying the drag decrease at low angles of attack produced by tail size reductions was the primary focus. The model was tested at Mach numbers of 0.40, 0.90, and 1.20 over an angle of attack of -2 degree to 10 degree. The nozzle exhaust flow was simulated using high pressure air at nozzle pressure ratios varying from 1.0 (jet off) to 7.5. Data were obtained on the baseline configuration with and without tails as well as with reduced horizontal and/or vertical tail sizes that were 75, 50, and 25 percent of the baseline tail areas. |
| File Size | 15054957 |
| Page Count | 59 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19900016622 |
| Archival Resource Key | ark:/13960/t5cc5x01x |
| Language | English |
| Publisher Date | 1990-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Tail Assemblies Canard Configurations Transonic Wind Tunnels Two Dimensional Flow F-15 Aircraft Nozzle Geometry Drag Nozzle Flow Stabilizers Fluid Dynamics Pressure Ratio Angle of Attack Aerodynamic Characteristics 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 |
