Bleed system design technology for supersonic inlets

Journal of Aircraft

Volumn 10, Issue 7, 1973, Pages 407-413

  Syberg, Jan ^a   Koncsek, Joseph L ^a  

^a BOEING COMPANY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

EID: 85003347124     PISSN: 00218669     EISSN: None     Source Type: Journal    
DOI: 10.2514/3.60241     Document Type: Article

References (7)

1. Syberg, J. and Koncsek, J. L., “Transonic and Supersonic Test of the SST Prototype Air Intake,” Rept. FAA-SS-72-50, April 1972, Federal Aviation Administration, Washington, D.C.
2. Koncsek, J. L. and Syberg, J., “Transonic and Supersonic Test of a Mach 2.65 Mixed-Compression Axisymmetric Intake,” CR-1977, March 1972, NASA.
3. Syberg, J. and Hickcox, T. E., “Design of a Bleed System for a Mach 3.5 Inlet,” CR-2187, Jan. 1973, NASA.
4. Reyhner, T. A., “A Computer Program for Finite Difference Calculation of Compressible Turbulent Boundary Layers,” D6-23236, 1970, The Boeing Co., Seattle, Wash.
5. Reyhner, T. A. and Hickcox, T. E., “A Procedure for Combined Viscous-Inviscid Analysis of Supersonic Inlet Flowfields,” Journal of Aircraft, Vol. 9, No. 8, Aug. 1972, pp. 589-595.
6. Dennard, J. S., “A Transonic Investigation of the Mass-Flow and Pressure Recovery Characteristics of Several Types of Auxiliary Air Inlets,” RM L57B07, 1957, NACA.
7. McLafferty, G. and Ranard, E., “Pressure Losses and Flow Coefficients of Slanted Perforations Discharging from Within a Simulated Supersonic Inlet,” R-0920-1, 1958, United Aircraft Corp., East Hartford, Conn.