The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST AUGMENTATION,...
The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility of achieving these objectives. The 'Jetwing'...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility of achieving these objectives. The 'Jetwing'...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility of achieving these objectives. The 'Jetwing'...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility of achieving these objectives. The 'Jetwing'...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility of achieving these objectives. The 'Jetwing'...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility of achieving these objectives. The 'Jetwing'...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility of achieving these objectives. The 'Jetwing'...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility of achieving these objectives. The 'Jetwing'...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
The need for military aircraft that will operate from short unimproved airfields, and the decks of smaller aircraft carriers has increased in recent years due to a changing world situation and the shrinking of the dollar. Such aircraft need to be fuel efficient, quiet, maneuverable, have low infrared signature, and carry a large useful load. The Ball-Bartoe 'Jetwing' is a single engine upper surface blowing concept which offers the possibility of achieving these objectives. The 'Jetwing'...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
Topics: DTIC Archive, Kimberlin, Ralph d, TENNESSEE UNIV SPACE INST TULLAHOMA, *JET AIRCRAFT, *SHORT...
The flow features developing over a two-element NACA 0012 airfoil, with the rear portion serving as a trailing edge flap, were investigated using dye flow visualization in the NPS water tunnel. The original motivation for the work arose from a need to identify any potential to enhance maneuverability of aircraft to enable smoother landing under adverse flight situations. The flap portion was maneuvered in two different unsteady motion histories by a drive mechanism: a constant pitch rate motion...
Topics: DTIC Archive, Gonzalez,Edgar E, Naval Postgraduate School Monterey United States, unsteady...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. (Author)
Topics: DTIC Archive, Cassel,L A, SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV,...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
The Air Force Armament Laboratory (AFATL) and the Arnold Engineering Development Center (AEDC) are participating in a joint effort to develop a trajectory control test vehicle (TCTV). The vehicle is to be used as a test bed for various seeker, autopilot, and flap actuator systems now in development. The aerodynamic characteristics of the vehicle were obtained from wind tunnel tests using a 0.25-scale model and are presented for Mach numbers 0.5 to 1.05 at angles of attack to 20 deg. The control...
Topics: DTIC Archive, Kaupp, H, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *GUIDED BOMBS, *GUIDED...
Wind tunnel tests were conducted on a 0.25-scale model to determine the static stability and control characteristics of the Super HOBOS/MK-84 (EOGB- II) munition. The tests were performed in the Aerodynamic Wind Tunnel (4T) over a Mach number range from 0.4 to 1.6 at angles of attack from -4 to 26 deg. Aerodynamic coefficients and control effectiveness data are presented. Two techniques, one using multiple flap deflections and the other single flap deflections, were employed during the test. A...
Topics: DTIC Archive, Smith, D K, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *GUIDED BOMBS,...
The initial series of wind tunnel tests which were designed to demonstrate the aerodynamic advantages of an advanced technology variable camber wing have been completed. These tests were conducted during twenty-four shifts of occupancy time at the NASA Ames 14-foot transonic wind tunnel between May 21 and June 15, 1973. The configurations tested consisted of the basic F-8, the F-8 with an advanced technology wing, the advanced wing with simple hinged leading and trailing edge flaps and various...
Topics: DTIC Archive, BOEING AEROSPACE CO SEATTLE WA, *CAMBER, *LEADING EDGE FLAPS, LOAD DISTRIBUTION,...
The aeroelastic phenomena associated with prop/rotor systems are discussed and classified. It is concluded that an acceptable technology exists in several areas, including wing/rotor divergence, whirl flutter, aeromechanical instability, and air and ground resonance. The technology is less successful in those areas where the flow through the rotor is significantly nonaxial, e.g., tilt-rotor transition regime and high-speed helicopter flight; also when forms of intermodal blade coupling exist...
Topics: DTIC Archive, Alexander, H R, BOEING VERTOL CO PHILADELPHIA PA, *ROTOR BLADES(ROTARY WINGS),...
Contents: Jet Noise Suppressor Configurations and Parametric Studies (Concluded) -- Acoustic ejectors on tube and conical nozzles, and Annular plug nozzle suppressor model studies; System studies -- Choked inlet - GE4 engine, Exhust nozzle open area schedule - GE4 Engine, and Tubomachinery noise on GE4 engine; General Electric Corporate Research and Development Center's Fundamental Jet Noise Work -- Supersonic jet noise suppression results and prediction methods.
Topics: DTIC Archive, Brausch, J F, FEDERAL AVIATION ADMINISTRATION WASHINGTON DC OFFICE OF SUPERSONIC...
A development program for a commercial supersonic aircraft and engines was sponsored by the Federal Aviation Administration during a five-year period from 1966 through 1971. The unique propulsion system, an afterburning turbojet, required acoustic suppression techniques to reduce its noise levels to those federally regulated for subsonic aircraft. An acoustic suppression research program was conducted by the General Electric Company to develop technology applicable to prototype and commercial...
Topics: DTIC Archive, Brausch, J F, GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP, *JET...
Results of the study indicate that, for an externally blown flap transport aircraft and missions investigated, aircraft gross weight reductions of 9% to 12.5% can be obtained from the utilization of turbofan engines incorporating Advanced Technology Components. Engine thrust/weight ratio was clearly the most significant propulsion design parameter in terms of providing aircraft weight reductions. Other propulsion parameters such as cruise SFC, bypass ratio, and overall pressure ratio had only...
Topics: DTIC Archive, Krabal, Richard J, AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OH, *JET...
The purpose of the study was to develop a unified analytical procedure to evaluate the effects of passive high-lift devices on deflected- slipstream or tilt-wing V/STOL configurations. Methods were developed to predict the two-dimensional flapped airfoil characteristics to be used in a span load program. The span load results are used in procedures for estimating the coefficients of lift, longitudinal force, and moment for a wing partially immersed in a propeller slipstream. These...
Topics: DTIC Archive, Hebert, J, GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV, *LIFT, *VERTICAL TAKEOFF...
All types of high-lift devices are covered. Both experimental and theoretical topics are reviewed, and the selected reports are listed by a subject and an author index.
Topics: DTIC Archive, Hebert, Jr , Joseph, GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV, *LIFT, *VERTICAL...
