Use of a translating cowl on a SSBJ for improved takeoff performance

Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting

Volumn 1, Issue , 2007, Pages 187-195

  Garzon, G Andres ^a,b,c  

^a Aerion Corporation   (United States)

^b AIAA ^*  (United States)

^c AIAA   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

BUSINESS JET; SUPERSONIC INLET GEOMETRY;

COMPUTATIONAL FLUID DYNAMICS; EQUATIONS OF MOTION; OPTIMIZATION; SUPERSONIC AERODYNAMICS; TAKEOFF;

JET ENGINES;

EID: 34250840141     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (12)

1. National Geospatial-Intelligence Agency, Digital Aeronautical Flight Information File - PFPS_3.3.1_ed7, https://164.214.2.62/dafif/dafif_0602_ed7/ - Raw data processed at Aerion Corporation.
2. th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 2006.
3. th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Albany, NY, August 2004.
4. th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 2007.
5. Mitchell, G., Campbell, R., Performance of a supersonic ramp-type side inlet with ram-scoop throat bleed and varying fuselage boundary layer removal mach number range 1.2 to 2.0, NACA RM-E56I26, January 1957.
6. Obery, L. J., Englert G. W., Nussdorfer, T. J., Pressure recovery, drag and subcritical stability characteristics of conical supersonic diffusers with boundary layer removal, NACA RM-E51H29, February 1952.
7. Smeltzer, D., Sorensen N., Tests of a mixed compression axisymmetric inlet with large transonic mass flow at mach numbers 0.6 to 2.65, NASA TN-D6971, December 1972.
8. th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 2006.
9. Henne, P.A., "Low speed test of translating lip axisymmetric inlets for subsonic transports" NASA Contractor Report CR-2467, September 1974.
10. Cortright, E., Preliminary investigation of a translating cowl technique for improving take-off performance of a sharp lip supersonic diffuser, NACA-RM-E51I24, November 1951.
11. Connors, J., Vise, G., Performance of a translating-double-cone axisymmetric inlet with cowl bypass at mach numbers from 2.0 to 3.5. NACA RM-E57H07b, November 1957.
12. Society of Automotive Engineers. Gas Turbine Engine Inlet Flow Distortion Guidelines, Aerospace Recommended Practice (ARP) 1420, 1978.