Author: E. Claude Jr Sanders
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Damping in Roll of Models with 45 Degree, 60 Degree, and 70 Degree Delta Wings Determined at High Subsonic, Transonic, and Supersonic Speeds with Rocket-powered Models
Author: E. Claude Jr Sanders
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Damping in Roll of Models with 45©, 60©, and 70© Delta Wings Determined at High Subsonic, Transonic, and Supersonic Speeds with Rocket -powered Models
Author: E. Claude Sanders
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26
Book Description
Experimental Determination of the Effects of Frequency and Amplitude of Oscillation on the Roll-stability Derivatives for a 60 Degree Delta-wing Airplane Model
Author: Lewis R. Fisher
Publisher:
ISBN:
Category : Vibration
Languages : en
Pages : 58
Book Description
Publisher:
ISBN:
Category : Vibration
Languages : en
Pages : 58
Book Description
Supersonic Flutter of a 60© Delta Wing Encountered During the Flight Test of a Rocket-propelled Model
Author: William T. Lauten
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26
Book Description
An analysis of the flight time-history records of a record-propelled 60 degree delta-wing airplane configuration indicate that wing flutter started during the accelerating portion of the flight at a Mach number of approximately 1.7 and continued through the peak Mach number of the test (M = 2.08) and during deceleration at least until telemeter failure at M = 1.4 and probably to an even lower speed. CW Doppler velocimeter data indicated that the wings did not fail during the flight.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26
Book Description
An analysis of the flight time-history records of a record-propelled 60 degree delta-wing airplane configuration indicate that wing flutter started during the accelerating portion of the flight at a Mach number of approximately 1.7 and continued through the peak Mach number of the test (M = 2.08) and during deceleration at least until telemeter failure at M = 1.4 and probably to an even lower speed. CW Doppler velocimeter data indicated that the wings did not fail during the flight.
Transonic Pitch Damping of a Delta Wing Aircraft Determined from Flight Measurements
Author: R. A. Feik
Publisher:
ISBN: 9780724132317
Category : Airplanes
Languages : en
Pages : 26
Book Description
A flight investigation aimed mainly at determining the pitch damping of a 60 degree Delta wing aircraft between M = 0.7 and M = 1.2 has been undertaken. Flight tests were conducted by ARDU and the measurements obtained have been successfully analysed at ARL using a modified Newton-Raphson parameter estimation procedure. The results for pitch damping as well as other longitudinal aerodynamic derivatives have been compared with wind tunnel and/or theoretical estimates. Further information has also been gained relating to the necessary conditions for successful extraction of parameters from flight data. The parameter estimation procedure has proved to be an effective analysis method even when only a modest amount of flight data, obtained using a relatively simple instrumentation package, has been available. (Author).
Publisher:
ISBN: 9780724132317
Category : Airplanes
Languages : en
Pages : 26
Book Description
A flight investigation aimed mainly at determining the pitch damping of a 60 degree Delta wing aircraft between M = 0.7 and M = 1.2 has been undertaken. Flight tests were conducted by ARDU and the measurements obtained have been successfully analysed at ARL using a modified Newton-Raphson parameter estimation procedure. The results for pitch damping as well as other longitudinal aerodynamic derivatives have been compared with wind tunnel and/or theoretical estimates. Further information has also been gained relating to the necessary conditions for successful extraction of parameters from flight data. The parameter estimation procedure has proved to be an effective analysis method even when only a modest amount of flight data, obtained using a relatively simple instrumentation package, has been available. (Author).
Subject Index to Unclassified ASTIA Documents
Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 308
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 308
Book Description
Flight Investigation at Subsonic, Transonic, and Supersonic Velocities of the Hinge-moment Characteristics, Lateral-control Effectiveness, and Wing Damping in Roll of a 60 Degrees Sweptback Delta Wing with Half-delta Tip Ailerons
Author: C. William Martz
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Experimental Determination of the Effects of Frequency and Amplitude of Oscillation on the Roll-stability Derivatives for a 60 Degree Delta-wing Airplane Model
Author: Lewis R. Fisher
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Aero/space Engineering
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1486
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1486
Book Description
Effect of Wing Flexibility on the Damping in Roll of a Notched Delta Wing Body Combination Between Mach Numbers 0.6 and Approximately 2.2 as Determined with Rocket-propelled Models
Author: William M. Bland
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description