Author: Glen A. MitchellPublisher:
ISBN:
Category : Vortex generators
Languages : en
Pages : 44
Book Description
Performance of Centerbody Vortex Generators in an Axisymmetric Mixed-compression Inlet at Mach Numbers from 2.0 to 3.0
Author: Glen A. MitchellPublisher:
ISBN:
Category : Vortex generators
Languages : en
Pages : 44
Book Description
NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information DivisionPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 472
Book Description
A Selected Listing of NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information DivisionPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 470
Book Description
Tests of a Mixed Compression Axisymmetric Inlet with Large Transonic Mass Flow at Mach Numbers 0.6 to 2.65
Author: Donald B. SmeltzerPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 196
Book Description
A 38.8-cm (15.28-in.) capture diameter model of a mixed-compression axisymmetric inlet system with a translating cowl was designed and tested. The internal contours, designed for Mach number 2.65, provided a throat area of 59 percent of the capture area when the cowl was retracted for transonic operation. Other model features included a boundary-layer removal system, vortex generators, an engine airflow bypass system, cowl support struts, and rotating rakes at the engine face. All tunnel testing was conducted at a tunnel total pressure of about 1 atm (a unit Reynolds number of about 8.53 million/m at Mach number 2.65) at angles of attack from 0 deg to 4 deg. Results for the following were obtained: total-pressure recovery and distortion at the engine face as a function of bleed mass-flow ratio, the effect of bleed and vortex generator configurations on pressure recovery and distortion, inlet tolerance to unstart due to changes in angle of attack or Mach number, surface pressure distributions, boundary-layer profiles, and transonic additive drag. At Mach number 2.65 and with the best bleed configurations, maximum total pressure recovery at the engine face ranged from 91 to 94.5 percent with bleed mass-flow ratios from 4 to 9 percent, respectively, and total-pressure distortion was less than 10 percent. At off-design supersonic Mach numbers above 1.70, maximum total-pressure recoveries and corresponding bleed mass flows were about the same as at Mach number 2.65, with about 10 to 15 percent distortion. In the transonic Mach number range, total pressure recovery was high (above 96 percent) and distortion was low (less than 15 percent) only when the inlet mass-flow ration was reduced 0.02 to 0.06 from the maximum theoretical value (0.590 at Mach number 1.0).
Scientific and Technical Aerospace Reports
Author: NASA SP.
Author: AIAA Journal
Author: American Institute of Aeronautics and AstronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1364
Book Description
Pandex Current Index to Scientific and Technical Literature
Author: Scramjet Propulsion
Author: E. T. CurranPublisher: AIAA
ISBN: 9781600864414
Category : Airplanes
Languages : en
Pages : 1354
Book Description
Experimental Investigation of a Large-scale, Two-dimensional, Mixed-compression Inlet System
Author: Norman D. WongPublisher:
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.