Author: Donald B. Smeltzer
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 162
Book Description
Investigation of a Nearly Isentropic Mixed-compression Axisymmetric Inlet System at Mach Numbers 0.6 to 3.2
Author: Donald B. Smeltzer
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 162
Book Description
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 162
Book Description
Investigation of a Mixed-compression Axisymmetric Inlet System at Mach Numbers 0.6 to 3.5
Author: Donald B. Smeltzer
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 252
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 252
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 344
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 344
Book Description
Analytic and Experimental Performace of Two Isentropic Mixed Compression Axisymmetric Inlets at Mach Numbers 0.8 to 2.65
Author: Donald B. Smeltzer
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
Book Description
Experimental Investigation of a Large-scale, Two-dimensional, Mixed-compression Inlet System
Author: Norman D. Wong
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 68
Book Description
A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 68
Book Description
A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.
NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 478
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 478
Book Description
Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of about 3.8
Author: John H. Lundell
Publisher:
ISBN:
Category : Propulsion systems
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Propulsion systems
Languages : en
Pages : 38
Book Description
A Selected Listing of NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 436
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 436
Book Description
Analytic and Experimental Performance of Two Isentropic Mixed Compression Axisymmetric Inlets at Mach Numbers 0.8 to 2.65
Author: Donald B. Smeltzer
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description
A mixed compression axisymmetric inlet model with a capture diameter of 50 cm was tested at Mach numbers ranging from 0.8 to 2.65 at 0 deg angle of attack and a constant total pressure of approximately 1 atm. Analytical methods accounting for the effects of both viscous and inviscid flows and incorporating empirical bleed discharge coefficients were used in the procedure for designing the inlet contours and the bleed system. Experimental results are compared with analytic predictions and are also compared with results from earlier tests of an inlet with the same internal contours but with a bleed system developed by cut and try methods in the wind tunnel. With the bleed configuration predicted by the design procedure, maximum total pressure recovery at the engine face at the design Mach number of 2.65 was 93 percent, with a total pressure distortion less than 10 percent. Corresponding bleed mass flow was approximately 7.5 percent, which was about 1.3 percent less than predicted. At lower supersonic Mach numbers, pressure recovery and bleed were generally lower and distortion generally higher.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description
A mixed compression axisymmetric inlet model with a capture diameter of 50 cm was tested at Mach numbers ranging from 0.8 to 2.65 at 0 deg angle of attack and a constant total pressure of approximately 1 atm. Analytical methods accounting for the effects of both viscous and inviscid flows and incorporating empirical bleed discharge coefficients were used in the procedure for designing the inlet contours and the bleed system. Experimental results are compared with analytic predictions and are also compared with results from earlier tests of an inlet with the same internal contours but with a bleed system developed by cut and try methods in the wind tunnel. With the bleed configuration predicted by the design procedure, maximum total pressure recovery at the engine face at the design Mach number of 2.65 was 93 percent, with a total pressure distortion less than 10 percent. Corresponding bleed mass flow was approximately 7.5 percent, which was about 1.3 percent less than predicted. At lower supersonic Mach numbers, pressure recovery and bleed were generally lower and distortion generally higher.
Performance of Three Isentropic All Internal Compression Axisymmetric Inlets Designed for Mach 2.5
Author: Bernhard H. Anderson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
Book Description