Author: Lawrence L. GaligherPublisher:
ISBN:
Category : Jet nozzles
Languages : en
Pages : 128
Book Description
Evaluation of Various Exhaust Nozzles at Free-stream Mach Numbers from 0.6 To. 3.0
Author: Lawrence L. GaligherPublisher:
ISBN:
Category : Jet nozzles
Languages : en
Pages : 128
Book Description
Evaluation of Various Exhaust Nozzles at Free-stream Mach Numbers from 0.6 To. 3.0
Author: Lawrence L. GaligherPublisher:
ISBN:
Category : Jet nozzles
Languages : en
Pages : 0
Book Description
Pitot Survey of Exhaust Flow Field of a 2-D Scramjet Nozzle at Mach 6 with Air Or Freon and Argon Used for Exhaust Simulation
Author: William J. MontaPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 40
Book Description
APSI/Advanced Exhaust Nozzle Test Results at Mach Numbers from 0.6 to 1.5
Author: Ernest J. LucasPublisher:
ISBN:
Category :
Languages : en
Pages : 120
Book Description
A test program was conducted in the Propulsion Wind Tunnel to obtain force and moment and surface pressure data on a 0.096-scale model of a proposed tactical aircraft. The force data were acquired with two separate internal balances, which measured the aircraft and the nozzle thrust-minus-drag loads, respectively. Results were obtained for two axisymmetric and four nonaxisymmetric nozzles at three simulated power settings. Nozzle deflections were simulated to define the change in maneuverability to be gained by vectoring the simulated exhaust jet. In addition to the simulated powered configurations, an open inlet flow-through reference configuration was tested to determine the basic airframe aerodynamics with forward and aft wing placements. The tests were conducted at Mach number from 0.6 to 1.5 at a free-stream Reynols number of 2.5 million/ft. Angle of attack was varied from -1 to 16 deg at nozzle pressure ratios from 1.0 (jet-off) to 20. (Author).
Scientific and Technical Aerospace Reports
Author: Technical Abstract Bulletin
Author: Thrust Performance of Isolated Plug Nozzles with Two Types of 40-spoke Noise Suppressor at Mach Numbers from 0 to 0.45
Author: Douglas E. HarringtonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
Book Description
Plug nozzles with two types of 40-spoke noise suppressor were tested at free-stream Mach numbers from 0 to 0.45 and over a range of nozzle pressure ratios from 1.5 to 4.0. In addition, an unsuppressed plug nozzle and a Supersonic Tunnel Association nozzle were also tested to provide baseline levels of thrust performance. The unsuppressed plug nozzle had an efficiency of 98 percent at an assumed takeoff pressure ratio of 3.0 and at Mach 0.36. At the same condition the suppressor nozzles had efficiencies of approximately 83.5 percent.
Monthly Catalog of United States Government Publications
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1388
Book Description
Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0.45
Author: Douglas E. HarringtonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
Book Description
Author: