Download or read book Aerodynamic Control of NASP type Vehicles Through Vortex Manipulation written by T. Ng and published by . This book was released on 1990 with total page 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 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 Aerodynamic Control of NASP type Vehicles Through Vortex Manipulation Volume 2 Static Wind Tunnel Tests written by and published by . This book was released on 1993 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Control of Nasp Type Vehicles Through Vortex Manipulation Volume 1 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 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Water tunnel tests were conducted on a NASP-type configuration to evaluate different pneumatic Forebody Vortex Control (FVC) methods. Flow visualization and yawing moment measurements were performed at angles of attack from 0 deg to 30 deg. The pneumatic techniques tested included jet and slot blowing. In general, blowing can be used efficiently to manipulate the forebody vortices at angles of attack greater than 20 deg. These vortices are naturally symmetric up to alpha = 25 deg and asymmetric between 25 deg and 30 deg angle of attack. Results indicate that tangential aft jet blowing is the most promising method for this configuration. Aft jet blowing produces a yawing moment towards the blowing side and the trends with blowing rate are well behaved. The size of the nozzle is not the dominant factor in the blowing process; the change in the blowing 'momentum, ' i.e., the product of the mass flow rate and the velocity of the jet, appears to be the important parameter in the water tunnel (incompressible and unchoked flow at the nozzle exit). Forward jet blowing is very unpredictable and sensitive to mass flow rate changes. Slot blowing (with the exception of very low blowing rates) acts as a flow 'separator'; it promotes early separation on the blow side, producing a yawing moment toward the non-blowing side for the C(sub mu) range investigated. Suarez, Carlos J. and Ng, T. Terry and Ong, Lih-Yenn and Malcolm, Gerald N. Unspecified Center..

Download or read book Aerodynamic Control of Nasp Type Vehicles Through Vortex Manipulation Volume 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt: Forebody Vortex Control (FVC) was explored in this research program for potential application to a NASP-type configuration. Wind tunnel tests were conducted to evaluate a number of jet blowing schemes. The configuration tested has a slender forebody and a 78 deg swept delta wing. Blowing jets were implemented on the leeward side of the forebody with small circular tubes tangential to the surface that could be directed aft, forward, or at angles in between. The effects of blowing are observed primarily in the yawing and rolling moments and are highly dependent on the jet configuration and the angle of attack. Results show that the baseline flow field, without blowing activated, is quite sensitive to the geometry differences of the various protruding jets, as well as being sensitive to the blowing, particularly in the angle of attack range where the forebody vortices are naturally asymmetric. The time lag of the flow field response to the initiation of blowing was also measured. The time response was very short, on the order of the time required for the flow disturbance to travel the distance from the nozzle to the specific airframe location of interest at the free stream velocity. Overall, results indicate that sizable yawing and rolling moments can be induced with modest blowing levels. However, direct application of this technique on a very slender forebody would require thorough wind tunnel testing to optimize the jet location and configuration. Suarez, Carlos J. and Kramer, Brian R. and Smith, Brooke C. and Malcolm, Gerald N. Unspecified Center AERODYNAMIC CONFIGURATIONS; BLOWING; CONTROL SURFACES; FLOW DISTRIBUTION; STATIC TESTS; VORTICES; WIND TUNNEL TESTS; AIRCRAFT CONTROL; DELTA WINGS; FOREBODIES; SWEPT WINGS...

Download or read book Aerodynamic Control of Nasp Type Vehicles Through Vortex Manipulation written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 156 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. Unspecified Center 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 Aerodynamic Control of Nasp Type Vehicles Through Vortex Manipulation Volume 3 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: Free-to-roll tests were conducted in water and wind tunnels in an effort to investigate the mechanisms of wing rock on a NASP-type vehicle. The configuration tested consisted of a highly-slender forebody and a 78 deg swept delta wing. In the water tunnel test, extensive flow visualization was performed and roll angle histories were obtained. In the wind tunnel test, the roll angle, forces and moments, and limited forebody and wing surface pressures were measured during the wing rock motion. A limit cycle oscillation was observed for angles of attack between 22 deg and 30 deg. In general, the experiments confirmed that the main flow phenomena responsible for the wing-body-tail wing rock are the interactions between the forebody and the wing vortices. The variation of roll acceleration (determined from the second derivative of the roll angle time history) with roll angle clearly slowed the energy balance necessary to sustain the limit cycle oscillation. Different means of suppressing wing rock by controlling the forebody vortices using small blowing jets were also explored. Steady blowing was found to be capable of suppressing wing rock, but significant vortex asymmetrices are created, causing the model to stop at a non-zero roll angle. On the other hand, alternating pulsed blowing on the left and right sides of the fore body was demonstrated to be a potentially effective means of suppressing wing rock and eliminating large asymmetric moments at high angles of attack. Suarez, Carlos J. and Smith, Brooke C. and Kramer, Brian R. and Ng, T. Terry and Ong, Lih-Yenn and Malcolm, Gerald N. Unspecified Center BLOWING; BODY-WING AND TAIL CONFIGURATIONS; DELTA WINGS; FLOW VISUALIZATION; SWEPT WINGS; VORTICES; WATER TUNNEL TESTS; WIND TUNNEL TESTS; ANGLE OF ATTACK; CONTROL SURFACES; PRESSURE; ROLL...

Download or read book Aerodynamic Control of NASP Type Vehicles Through Vortex Manipulation Volume 3 Wing Rock Experiments written by National Aeronautics and Space Administration NASA and published by . This book was released on 2018-11-13 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: Free-to-roll tests were conducted in water and wind tunnels in an effort to investigate the mechanisms of wing rock on a NASP-type vehicle. The configuration tested consisted of a highly-slender forebody and a 78 deg swept delta wing. In the water tunnel test, extensive flow visualization was performed and roll angle histories were obtained. In the wind tunnel test, the roll angle, forces and moments, and limited forebody and wing surface pressures were measured during the wing rock motion. A limit cycle oscillation was observed for angles of attack between 22 deg and 30 deg. In general, the experiments confirmed that the main flow phenomena responsible for the wing-body-tail wing rock are the interactions between the forebody and the wing vortices. The variation of roll acceleration (determined from the second derivative of the roll angle time history) with roll angle clearly slowed the energy balance necessary to sustain the limit cycle oscillation. Different means of suppressing wing rock by controlling the forebody vortices using small blowing jets were also explored. Steady blowing was found to be capable of suppressing wing rock, but significant vortex asymmetrices are created, causing the model to stop at a non-zero roll angle. On the other hand, alternating pulsed blowing on the left and right sides of the fore body was demonstrated to be a potentially effective means of suppressing wing rock and eliminating large asymmetric moments at high angles of attack. Suarez, Carlos J. and Smith, Brooke C. and Kramer, Brian R. and Ng, T. Terry and Ong, Lih-Yenn and Malcolm, Gerald N. Unspecified Center BLOWING; BODY-WING AND TAIL CONFIGURATIONS; DELTA WINGS; FLOW VISUALIZATION; SWEPT WINGS; VORTICES; WATER TUNNEL TESTS; WIND TUNNEL TESTS; ANGLE OF ATTACK; CONTROL SURFACES; PRESSURE; ROLL...

Download or read book Aerodynamic Control of NASP type Vehicles Through Vortex Manipulation Volume 1 Static Water Tunnel Tests written by and published by . This book was released on 1993 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 728 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Annual Index written by and published by . This book was released on 1994 with total page 1372 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements Index written by and published by . This book was released on 1994 with total page 694 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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Download or read book Monthly Catalogue United States Public Documents written by and published by . This book was released on 1994 with total page 1020 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Finding Guide to AIAA Meeting Papers written by American Institute of Aeronautics and Astronautics. Technical Information Service and published by . This book was released on 1990 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt: