Download or read book Aerodynamic Control Using Forebody Strakes written by T. Terry Ng and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Method for Integrating Thrust Vectoring and Actuated Forebody Strakes with Conventional Aerodynamic Controls on a High Performance Fighter Airplane written by Frederick J. Lallman and published by . This book was released on 1998 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Investigations of Forebody Strakes for Yaw Control on F A 18 Model at Subsonic and Transonic Speeds written by Gary E. Erickson and published by . This book was released on 1993 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Subsonic Fore body Aerodynamic Control Using Rotable Miniature Strakes written by and published by . This book was released on 1998 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Method for Integrating Thrust Vectoring and Actuated Forebody Strakes with Conventional Aerodynamic Controls on a High Performance Fighter Airplane written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-28 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method, called pseudo controls, of integrating several airplane controls to achieve cooperative operation is presented. The method eliminates conflicting control motions, minimizes the number of feedback control gains, and reduces the complication of feedback gain schedules. The method is applied to the lateral/directional controls of a modified high-performance airplane. The airplane has a conventional set of aerodynamic controls, an experimental set of thrust-vectoring controls, and an experimental set of actuated forebody strakes. The experimental controls give the airplane additional control power for enhanced stability and maneuvering capabilities while flying over an expanded envelope, especially at high angles of attack. The flight controls are scheduled to generate independent body-axis control moments. These control moments are coordinated to produce stability-axis angular accelerations. Inertial coupling moments are compensated. Thrust-vectoring controls are engaged according to their effectiveness relative to that of the aerodynamic controls. Vane-relief logic removes steady and slowly varying commands from the thrust-vectoring controls to alleviate heating of the thrust turning devices. The actuated forebody strakes are engaged at high angles of attack. This report presents the forward-loop elements of a flight control system that positions the flight controls according to the desired stability-axis accelerations. This report does not include the generation of the required angular acceleration commands by means of pilot controls or the feedback of sensed airplane motions. Lallman, Frederick J. and Davidson, John B. and Murphy, Patrick C. Langley Research Center RTOP 522-22-21-03...

Download or read book Effect of Actuated Forebody Strakes on the Forebody Aerodynamics of the NASA F 18 Harv written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-02 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Extensive pressure measurements and off-surface flow visualization were obtained on the forebody and strakes of the NASA F-18 High Alpha Research Vehicle (HARV) equipped with actuated forebody strakes. Forebody yawing moments were obtained by integrating the circumferential pressures on the forebody and strakes. Results show that large yawing moments can be generated with forebody strakes. At angles of attack greater than 40 deg., deflecting one strake at a time resulted in a forebody yawing moment control reversal for small strake deflection angles. At alpha = 40 deg. and 50 deg., deflecting the strakes differentially about a 20 deg. symmetric strake deployment eliminated the control reversal and produced a near linear variation of forebody yawing moment with differential strake deflection. At alpha = 50 deg. and for 0 deg. and 20 deg. symmetric strake deployments, a larger forebody yawing moment was generated by the forward fuselage (between the radome and the apex of the leading-edge extensions), than on the radome where the actuated forebody strakes were located. Cutouts on the flight vehicle strakes that were not on the wind tunnel models are believed to be responsible for deficits in the suction peaks on the flight radome pressure distributions and differences in the forebody yawing moments. Fisher, David F. and Murri, Daniel G. and Lanser, Wendy R. Unspecified Center RTOP 505-68-30...

Download or read book Using the HARV Simulation Aerodynamic Model to Determine Forebody Strake Aerodynamic Coefficients from Flight Data written by Michael D. Messina and published by . This book was released on 1995 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: The method described in this report is intended to present an overview of a process developed to extract the forebody aerodynamic increments from flight tests. The process to determine the aerodynamic increments (rolling pitching, and yawing moments, Cl, Cm, Cn, respectively) for the forebody strake controllers added to the F/A - 18 High Alpha Research Vehicle (HARV) aircraft was developed to validate the forebody strake aerodynamic model used in simulation.

Download or read book Low speed Wind tunnel Investigation of a Porous Forebody and Nose Strakes for Yaw Control of a Multirole Fighter Aircraft written by Scott P. Fears and published by . This book was released on 1995 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Control of NASP type Vehicles Through Vortex Manipulation Volume 4 written by and published by . This book was released on 1993 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Actuated Forebody Strakes on the Forebody Aerodynamics of the NASA F 18 HARV written by David F. Fisher and published by . This book was released on 1996 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Forebody Aerodynamics of the F 18 High Alpha Research Vehicle with Actuated Strakes written by and published by . This book was released on 2003 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt: Extensive pressure measurements and off-surface flow visualization were obtained on the forebody and strakes of the NASA F-18 High Alpha Research Vehicle (HARV) equipped with actuated forebody strakes. Forebody yawing moments were obtained by integrating the circumferential pressures on the forebody and strakes. Results show that large yawing moments can be generated with forebody strakes. At a 500-angle-of attack, deflecting one strake at a time resulted in a forebody yawing moment control reversal for small strake deflection angles. However, deflecting the strakes differentially about a 200 symmetric strake deployment eliminated the control reversal and produced a near linear variation of forebody yawing moment with differential strake deflection. At an angle of attack of 500 and for O% and 200 symmetric strake deployments, a larger forebody yawing moment was generated by the forward fuselage (between the radome and the apex of the leading-edge extensions) than on the radome where the actuated forebody strakes were located. Cutouts on the flight vehicle strakes that were not on the wind tunnel models are believed to be responsible for deficits in the suction peaks on the flight radome pressure distributions and differences in the forebody yawing moments.

Download or read book Roll yaw Control at High Angle of Attack by Forebody Tangential Blowing written by Nelson Pedreiro and published by . This book was released on 1995 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Control of NASP type Vehicles Through Vortex Manipulation Volume 3 Wing Rock Experiments written by and published by . This book was released on 1993 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Control of Nasp Type Vehicles Through Vortex Manipulation written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11-18 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt: Forebody Vortex Control (FVC) is an emerging technology that has received widespread and concentrated attention by many researchers for application on fighter aircraft to enhance aerodynamic controllability at high angles of attack. This research explores potential application of FVC to a NASP-type configuration. The configuration investigated is characterized by a slender, circular cross-section forebody and a 78 deg swept delta wing. A man-in-the-loop, six-degress-of-freedom, high-fidelity simulation was developed that demonstrates the implementation and advantages of pneumatic forebody vortex control. Static wind tunnel tests were used as the basis for the aerodynamic characteristics modeled in the simulation. Dynamic free-to-roll wind tunnel tests were analyzed and the wing rock motion investigated. A non-linear model of the dynamic effects of the bare airframe and the forebody vortex control system were developed that closely represented the observed behavior. Multiple state-of-the-art digital flight control systems were developed that included different utilizations of pneumatic vortex control. These were evaluated through manned simulation. Design parameters for a pneumatic forebody vortex control system were based on data collected regarding the use of blowing and the mass flow required during realistic flight maneuvers. Smith, Brooke C. and Suarez, Carlos J. and Porada, William M. and Malcolm, Gerald N. AERODYNAMIC CHARACTERISTICS; AIRCRAFT CONTROL; CONTROL SURFACES; CONTROLLABILITY; FLIGHT CONTROL; FLIGHT SIMULATION; VORTICES; ANGLE OF ATTACK; BLOWING; DELTA WINGS; DESIGN ANALYSIS; FIGHTER AIRCRAFT; SWEPT WINGS...

Download or read book Exploratory Investigation of Forebody Strakes for Yaw Control of a Generic Fighter with a Symmetric 60 Deg Half Angle Chine Forebody written by and published by . This book was released on 1997 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Investigations of Forebody Strakes for Yaw Control on F a 18 Model at Subsonic and Transonic Speeds written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-23 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel investigations have been conducted of forebody strakes for yaw control on 0.06-scale models of the F/A-18 aircraft at free-stream Mach numbers of 0.20 to 0.90. The testing was conducted in the 7- by 10-Foot Transonic Tunnel at the David Taylor Research Center and the Langley 7- by 10-Foot High-Speed Tunnel. The principal objectives of the testing were to determine the effects of the Mach number and the strake plan form on the strake yaw control effectiveness and the corresponding strake vortex induced flow field. The wind tunnel model configurations simulated an actuated conformal strake deployed for maximum yaw control at high angles of attack. The test data included six-component forces and moments on the complete model, surface static pressure distributions on the forebody and wing leading-edge extensions, and on-surface and off-surface flow visualizations. The results from these studies show that the strake produces large yaw control increments at high angles of attack that exceed the effect of conventional rudders at low angles of attack. The strake yaw control increments diminish with increasing Mach number but continue to exceed the effect of rudder deflection at angles of attack greater than 30 degrees. The character of the strake vortex induced flow field is similar at subsonic and transonic speeds. Cropping the strake planform to account for geometric and structural constraints on the F-18 aircraft has a small effect on the yaw control increments at subsonic speeds and no effect at transonic speeds. Erickson, Gary E. and Murri, Daniel G. Langley Research Center DIRECTIONAL CONTROL; F-18 AIRCRAFT; FLOW VISUALIZATION; FOREBODIES; STRAKES; SUBSONIC SPEED; TRANSONIC SPEED; VORTICES; WIND TUNNEL TESTS; YAW; AERODYNAMICS; ANGLE OF ATTACK; FLOW DISTRIBUTION; MACH NUMBER; PLANFORMS; PRESSURE DISTRIBUTION; STATIC PRESSURE; VORTEX BREAKDOWN; VORTEX GENERATORS; YAWING MOMENTS...

Download or read book Low Speed Wind Tunnel Investigation of a Porous Forebody and Nose Strakes for Yaw Control of a Multirole Fighter Aircraft written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-08 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Low-speed wind-tunnel tests were conducted in the Langley 12-Foot Low-Speed Tunnel on a model of the Boeing Multirole Fighter (BMRF) aircraft. This single-seat, single-engine configuration was intended to be an F-16 replacement that would incorporate many of the design goals and advanced technologies of the F-22. Its mission requirements included supersonic cruise without afterburner, reduced observability, and the ability to attack both air-to-air and air-to-ground targets. So that it would be effective in all phases of air combat, the ability to maneuver at angles of attack up to and beyond maximum lift was also desired. Traditional aerodynamic yaw controls, such as rudders, are typically ineffective at these higher angles of attack because they are usually located in the wake from the wings and fuselage. For this reason, this study focused on investigating forebody-mounted controls that produces yawing moments by modifying the strong vortex flowfield being shed from the forebody at high angles of attack. Two forebody strakes were tested that varied in planform and chordwise location. Various patterns of porosity in the forebody skin were also tested that differed in their radial coverage and chordwise location. The tests were performed at a dynamic pressure of 4 lb/ft(exp 2) over an angle-of-attack range of -4 deg to 72 deg and a sideslip range of -10 deg to 10 deg. Static force data, static pressures on the surface of the forebody, and videotapes of flow-visualization using laser-illuminated smoke were obtained. Fears, Scott P. Unspecified Center...