Aerodynamic Characteristics of a Vane Flow Angularity Sensor System Capable of Measuring Flightpath Accelerations for the Mach Number Range From 0.40 to 2.54. Technical Report NASA Technical Note TN D-8242, Research Engineering, NASA Dryden Flight Research Center
Sakamoto, Glenn M. (1976) Aerodynamic Characteristics of a Vane Flow Angularity Sensor System Capable of Measuring Flightpath Accelerations for the Mach Number Range From 0.40 to 2.54. Technical Report NASA Technical Note TN D-8242, Research Engineering, NASA Dryden Flight Research Center.
Full text available as: |
Abstract
This report presents the results of a wind tunnel investigation of the aerodynamic characteristics of a vane flow angularity sensor system capable of measuring flightpath accelerations. The aerodynamic characteristics of the angle of attack vane and the angle of sideslip vane are summarized. The test conditions ranged in free stream Mach number from 0.40 to 2.54, in angle of attack from -2 degrees to 22 degrees, in angle of sideslip from -2 degrees to 12 degrees, and in Reynolds number from 5.9 x 10 to the 6th power per meter (1.8 x 10 to the 6th power per foot) to 18.0 x 10 to the 6th power per meter (5.5 x 10 to the 6th power per foot). The results of the wind tunnel investigation are compared with results obtained with similar vane configurations. Comparisons with a NACA vane configuration are also made. In addition, wind tunnel-derived upwash for the test installation is compared with analytical predictions.
| EPrint Type: | Other |
|---|---|
| Keywords: | Wind tunnel tests, Vane flow direction sensors, Upwash corrections |
| Subjects: | Aircraft/Project: Nonaircraft-specific (01 - 09) Aeronautics: (06) Avionics And Aircraft Instrumentation |
| ID Code: | 706 |
| Deposited On: | 14 Febuary 2006 |
| Additional Information: | 45 pages. |
