Author: Bobby L. Berrier
Publisher:
ISBN:
Category :
Languages : en
Pages : 131
Book Description
Effect of Nozzle Lateral Spacing on Afterbody Drag and Performance of Twin-jet Afterbody Models with Cone Plug Nozzles at Mach Numbers Up to 2.20
Author: Bobby L. Berrier
Publisher:
ISBN:
Category :
Languages : en
Pages : 131
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 131
Book Description
Effect of Nozzle Lateral Spacing on Afterbody Drag and Performance of Twin-jet Afterbody Models with Convergent-divergent Nozzles at Mach Numbers Up to 2.2
Author: Odis C. Jr Pendergraft
Publisher:
ISBN:
Category :
Languages : en
Pages : 123
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 123
Book Description
Effect of Nozzle Lateral Spacing on Afterbody Drag and Performance of Twin-jet Afterbody Models with Convergent Nozzles at Mach Numbers Up to 2.2
Author: Donald L. Maiden
Publisher:
ISBN:
Category :
Languages : en
Pages : 148
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 148
Book Description
Effect of Nozzle Lateral Spacing, Engine Interfairing Shape, and Angle of Attack on the Performance of a Twin-jet Afterbody Model with Cone Plug Nozzles
Author: Bobby L. Berrier
Publisher:
ISBN:
Category :
Languages : en
Pages : 142
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 142
Book Description
Effect of Jet Velocity and Axial Location of Nozzle Exit on the Performance of a Twin-jet Afterbody Model at Mach Numbers Up to 2.2
Author: Bobbly Lee Berrier
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 84
Book Description
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 84
Book Description
Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range
Author: C. E. Robinson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 98
Book Description
Results of an experimental and analytical research investigation on nozzle/afterbody drag are presented. Experimental afterbody (and boattail) drag coefficients and pressure distributions are discussed for an isolated, strut-mounted nozzle/afterbody model for the Mach number range from 0.6 to 1.5. Some data are also given for free-stream unit Reynolds numbers from one million to approximately four million per foot. The experimental data were obtained for the basic model with an air-cooled and a water-cooled Ethylene/air combustor to provide hot-jet duplication as well as cold-jet simulation. The temperature of the nozzle exhaust gas was varied from 530R (burner-off) to approximately 2500R for several nozzle pressure ratios from jet-off to those corresponding to a moderately under-expanded exhaust plum. The initial series of experiments was conducted with the air-cooled combustors, and the effect of jet temperature on afterbody drag was somewhat masked by the effects of the secondary airflow from the cooling air. The general trend, however, shows a decreasing afterbody drag with increasing exhaust gas temperature and with decreasing secondary airflow at a fixed nozzle pressure ratio. (Modified author abstract).
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 98
Book Description
Results of an experimental and analytical research investigation on nozzle/afterbody drag are presented. Experimental afterbody (and boattail) drag coefficients and pressure distributions are discussed for an isolated, strut-mounted nozzle/afterbody model for the Mach number range from 0.6 to 1.5. Some data are also given for free-stream unit Reynolds numbers from one million to approximately four million per foot. The experimental data were obtained for the basic model with an air-cooled and a water-cooled Ethylene/air combustor to provide hot-jet duplication as well as cold-jet simulation. The temperature of the nozzle exhaust gas was varied from 530R (burner-off) to approximately 2500R for several nozzle pressure ratios from jet-off to those corresponding to a moderately under-expanded exhaust plum. The initial series of experiments was conducted with the air-cooled combustors, and the effect of jet temperature on afterbody drag was somewhat masked by the effects of the secondary airflow from the cooling air. The general trend, however, shows a decreasing afterbody drag with increasing exhaust gas temperature and with decreasing secondary airflow at a fixed nozzle pressure ratio. (Modified author abstract).
Interference Between Exhaust System and Afterbody of Twin-engine Fuselage Configurations
Author: Jack F. Runckel
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 52
Book Description
Effect of Convergent Ejector Nozzles on the Boattail Drag of a 16© Conical Afterbody at Mach Number of 0.6 to 1.26
Author: James M. Cubbage
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 38
Book Description
Effect of Base Bleed and Terminal Fairings on the Performance of Exhaust-nozzle-afterbody Combinations at Mach Numbers of 1.93, 2.55 and 3.05
Author: Harry T. Norton
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Performance of Closely Spaced Twin-jet Afterbodies with Different Inboard-outboard Fairing and Nozzle Shapes
Author: Edwin E. Lee (Jr.)
Publisher:
ISBN:
Category : Interference (Aeronautics)
Languages : en
Pages : 164
Book Description
Publisher:
ISBN:
Category : Interference (Aeronautics)
Languages : en
Pages : 164
Book Description