Author: Terry J. LarsonPublisher:
ISBN:
Category :
Languages : en
Pages : 68
Book Description
Qualitative Evaluation of a Flush Air Data System at Transonic Speeds and High Angles of Attack
Author: Terry J. LarsonPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 68
Book Description
Development of a Flush Airdata Sensing System on a Sharp-nosed Vehicle for Flight at Mach 3 to 8
Author: Mark C. DavisPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 28
Book Description
NASA Dryden Flight Research Center has developed a flush airdata sensing (FADS) system on a sharp-nosed, wedge-shaped vehicle. This paper details the design and calibration of a real-time angle-of-attack estimation scheme developed to meet the onboard airdata measurement requirements for a research vehicle equipped with a supersonic-combustion ramjet engine. The FADS system has been designed to perform in flights at speeds between Mach 3 and Mach 8 and at angles of attack between -6° and 12°. The description of the FADS architecture includes port layout, pneumatic design, and hardware integration. Predictive models of static and dynamic performance are compared with wind-tunnel results across Mach and angle-of-attack range. Results indicate that static angle-of-attack accuracy and pneumatic lag can be adequately characterized and incorporated into a real-time algorithm.
Design and Calibration of the X-33 Flush Airdata Sensing (FADS) System
Author: Stephen A. WhitmorePublisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 38
Book Description
NASA Technical Paper
Author: Flush Airdata Sensing (FADS) System Calibration Procedures and Results for Blunt Forebodies
Author: Brent R. CobleighPublisher:
ISBN:
Category : Aeronautical instruments
Languages : en
Pages : 34
Book Description
Blunt-forebody pressure data are used to study the behavior of the NASA Dryden Flight Research Center flush airdata sensing (FADS) pressure model and solution algorithm. The model relates surface pressure measurements to the airdata state. Spliced from the potential flow solution for uniform flow over a sphere and the modified Newtonian impact theory, the model was shown to apply to a wide range of blunt-forebody shapes and Mach numbers. Calibrations of a sphere, spherical cones, a Rankine half body, and the F-14, F/A-18, X-33, X-34, and X-38 configurations are shown. The three calibration parameters are well-behaved from Mach 0.25 to Mach 5.0, an angle-of-attack range extending to greater than 30 deg., and an angle-of-sideslip range extending to greater than 15 deg. Contrary to the sharp calibration changes found on traditional pitot-static systems at transonic speeds, the FADS calibrations are smooth, monotonic functions of Mach number and effective angles of attack and sideslip. Because the FADS calibration is sensitive to pressure port location, detailed measurements of the actual pressure port locations on the flight vehicle are required and the wind-tunnel calibration model should have pressure ports in similar locations. The procedure for calibrating a FADS system is outlined.
NASA Scientific and Technical Publications
Author: Scientific and Technical Aerospace Reports
Author: Monthly Catalogue, United States Public Documents
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1480
Book Description
Monthly Catalog of United States Government Publications
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1224
Book Description
Author: Stephen A. Whitmore