Author: H. E. McDill
Publisher:
ISBN:
Category : Eagle (Jet fighter plane)
Languages : en
Pages : 330
Book Description
Results of the Full-scale F-15 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers
Author: H. E. McDill
Publisher:
ISBN:
Category : Eagle (Jet fighter plane)
Languages : en
Pages : 330
Book Description
Publisher:
ISBN:
Category : Eagle (Jet fighter plane)
Languages : en
Pages : 330
Book Description
Results of the Full-scale F-15 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers
Author: H. E. McDill
Publisher:
ISBN:
Category : Eagle (Jet fighter plane).
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category : Eagle (Jet fighter plane).
Languages : en
Pages : 0
Book Description
Results of a Full-scale B-1 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers
Author: H. E. McDill
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 416
Book Description
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 416
Book Description
Index of Limited Documents Releasable to DTIC Users
Results of a Full-scale B-1 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers
Author: H. E. McDill
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 0
Book Description
Journal of Aircraft
Data Base for the Prediction of Airframe/propulsion System Interference Effects
Scientific and Technical Aerospace Reports
93-2168 - 93-2206
Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers
Author: John F. Riddell
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 250
Book Description
Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author).
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 250
Book Description
Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author).