Author: United States. National Aeronautics and Space AdministrationPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
A COMPARISON OF SIGNAL ENHANCEMENT METHODS FOR EXTRACTING TONAL ACOUSTIC SIGNALS... NASA/TM-1998-208426... AUG. 6, 1998
Author: United States. National Aeronautics and Space AdministrationPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
A Comparison of Signal Enhancement Methods for Extracting Tonal Acoustic Signals
Author: A Comparison of Signal Enhancement Methods for Extracting Tonal Acoustic Signals
Author: Michael G. JonesAIAA Journal
Author: American Institute of Aeronautics and AstronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 894
Book Description
Simulator Study of Stall/post-stall Characteristics of a Fighter Airplane with Relaxed Longitudinal Static Stability
Author: A Parametric Study of the Aerodynamic Characteristics of Nose-cylinder-flare Bodies at a Mach Number of 6.0
Author: George C. AshbyPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
Book Description
Studies of Airframe-propulsion-system Integration for Mach 6 Cruise Vehicles
Author: Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 26
Book Description
Summary of Flight-test Results of the VZ-2 Tilt-wing Aircraft
Author: Robert J. PeggPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
Book Description
Buckling of a Pressurized Toroidal Ring Under Uniform External Loading
Author: George E. WeeksPublisher:
ISBN:
Category : Buckling (Mechanics)
Languages : en
Pages : 28
Book Description
Investigation of Engine-exhaust-airframe Interference on a Cruise Vehicle at Mach 6
Author: James M. CubbagePublisher:
ISBN:
Category : Aircraft exhaust emissions
Languages : en
Pages : 76
Book Description
Results from an investigation of the effects of underexpanded engine exhaust flow on the aerodynamic performance and stability of a cruise airplane at Mach 6 are presented. The influence of wing reflex angle and nozzle geometry on exhaust flow interference effects was investigated on a flat-plate model. The experiments were conducted at a free-stream Reynolds number of 17.05 X 10 (to the 6 power) based on the length of the airplane model over a model angle-of-attack range of 0(degrees) to 10(degrees) and at nozzle static-pressure ratios from 1 to approximately 4.