Name: Performance and Flowfield Measurements on a 10-Inch Ducted Rotor Vtol Uav (en Inglés)
Price: 30300.00 CLP
Availability: InStock
Author: Martin, Preston ; Tung, Chee ; Nasa Technical Reports Server (Ntrs)
ISBN: 9781289277208

portada Performance and Flowfield Measurements on a 10-Inch Ducted Rotor Vtol Uav (en Inglés)

Formato

Libro Físico

Autor

Nasa Technical Reports Server (Ntrs)

Chee Tung

Preston Martin

Editorial

Bibliogov

Idioma

Inglés

N° páginas

Encuadernación

Tapa Blanda

Dimensiones

24.6 x 18.9 x 0.1 cm

Peso

0.06 kg.

ISBN13

9781289277208

Categorías

Política y gobierno

Performance and Flowfield Measurements on a 10-Inch Ducted Rotor Vtol Uav (en Inglés)

Nasa Technical Reports Server (Ntrs) (Autor) · Chee Tung (Autor) · Preston Martin (Autor) · Bibliogov · Tapa Blanda

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Origen: Estados Unidos (Costos de importación incluídos en el precio)

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Reseña del libro "Performance and Flowfield Measurements on a 10-Inch Ducted Rotor Vtol Uav (en Inglés)"

A ducted fan VTOL UAV with a 10-inch diameter rotor was tested in the US Army 7-by 10-Foot Wind Tunnel. The test conditions covered a range of angle of attack from 0 to 110 degrees to the freestream. The tunnel velocity was varied from 0 (simulating a hover condition) to 128 ft/sec in propeller mode. A six-component internal balance measured the aerodynamic loads for a range of model configurations. including the isolated rotor, the isolated duct, and the full configuration of the duct and rotor. For some conditions, hotwire velocity surveys were conducted along the inner and outer surface of the duct and across the downstream wake. In addition, fluorescent oil flow visualization allowed the flow separation patterns inside and outside of the duct to be mapped for a few test conditions. Two different duct shapes were tested to determine the performance effects of leading edge radius. For each duct, a range of rotor tip gap from 1%R to 4.5%R was tested to determine the performance penalty in hover and axial flight. Measured results are presented in terms of hover performance, hover performance in a crosswind, and high angle of attack performance in propeller mode. In each case, the effects of both tip gap and duct leading edge radius are illustrated using measurements. Some of the hover performance issues were also studied using a simple analytical method, and the results agreed with the measurements.