Download or read book Augmentation of Fighter Aircraft Performance by Spanwise Blowing Over the Wing Leading Edge written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-25 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Spanwise blowing over the wing and canard of a 1:35 model of a close-coupled-canard fighter airplane configuration (similar to the Kfir-C2) was investigated experimentally in low-speed flow. Tests were conducted at airspeeds of 30 m/sec (Reynolds number of 1.8 x 10 to the 5th power based on mean aerodynamic chord) with angle-of-attack sweeps from -8 to 60 deg, and yaw-angle sweeps from -8 to 36 deg at fixed angles of attack 0, 10, 20, 25, 30, and 35 deg. Significant improvement in lift-curve slope, maximum lift, drag polar and lateral/directional stability was found, enlarging the flight envelope beyond its previous low-speed/maximum-lift limit. In spite of the highly swept (60 deg) leading edge, the efficiency of the lift augmentation by blowing was relatively high and was found to increase with increasing blowing momentum on the close-coupled-canard configuration. Interesting possibilities of obtaining much higher efficiencies with swirling jets were indicated. Seginer, A. and Salomon, M. Ames Research Center NASA-TM-84330, A-9243, NAS 1.15:84330 RTOP 505-42-21
Download or read book Augmentation of Fighter aircraft Performance by Spanwise Blowing Over the Wing Leading Edge written by and published by . This book was released on 1983 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Spanwise blowing over the wing canard of a 1:35 model of a close-coupled-canard fighter-airplane configuration (similar to the Kfir-C2) was investigated experimentally in low-speed flow. Tests were conducted at airspeeds of 30 m/sec (Reynolds number of 180000 based on mean aerodynamic chord) with angle-of-attack sweeps form -8 deg to 60 deg, and yaw-angle sweeps from -8 deg to 36 deg at fixed angles of attack 0 deg, 10 deg, 20 deg, 25 deg, 30 deg, and 35 deg. Significant improvement in lift-curve slope, maximum lift, drag polar and lateral/limit. In spite of the highly swept (60 deg) leading edge, the efficiency of the lift augmentation by blowing was relatively high and was found to increase with increasing blowing momentum on the close-coupled-canard configuration. Interesting possibilities of obtaining much higher efficiencies with swirling jets were indicated. (Author).
Download or read book Augmentation of Maneuver Performance by Spanwise Blowing written by Gary Edward Erickson and published by . This book was released on 1977 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Improvement of Maneuver Aerodynamics by Spanwise Blowing written by Gary E. Erickson and published by . This book was released on 1977 with total page 72 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 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Blowing Spanwise from the Tips of Low Aspect Ratio Wings of Varying Taper Ratio with Application to Improving STOL Capability of Fighter Aircraft written by R. G. Schwind and published by . This book was released on 1983 with total page 93 pages. Available in PDF, EPUB and Kindle. Book excerpt: Parametric low-speed wind tunnel testing of several low aspect ratio half-span wings featuring outboard-blowing wing-tip jets has been accomplished. This effort was performed to extend the existing information base regarding lift augmentation of low aspect ratio wings to encompass tapered wings suitable for application to high-performance fighter aircraft. At an angle of attack typical for fighter aircraft takeoff, operation of the wing-tip jets was found to augment the lift coefficient of aspect ratio two wings by 25% to 35%, depending upon the value of the jet momentum coefficient and the wing taper ratio. At low angles of attack, the wing lift coefficients were augmented by as much as 120%, but the amount of lift augmentation decreased in inverse proportion to wing angle of attack. The worth of blowing outboard from the wing tips of fighter aircraft as a means of enhancing STOL performance was assessed. Diverting 70% of the engine bypass airflow to the wing tips reduced predicted takeoff and landing distances by 15%. Differential left-wing-tip-to-right-wing-tip modulation of the jet momentum can immediately produce up to 15,000 ft-lbs of additional roll control torque during low-speed landing approaches. (Author).
Download or read book NASA Technical Paper written by and published by . This book was released on 1985 with total page 814 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research and Technology Objectives and Plans Summary RTOPS written by and published by . This book was released on 1985 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1971 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Download or read book V STOL Concepts in the United States Past Present and Future written by and published by . This book was released on 1984 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by United States. National Aeronautics and Space Administration and published by . This book was released on 1977 with total page 634 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Proceedings of a Workshop on V STOL Aircraft Aerodynamics written by and published by . This book was released on 1979 with total page 484 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Vectored Propulsion Supermaneuverability and Robot Aircraft written by Benjamin Gal-Or and published by Springer Science & Business Media. This book was released on 2013-11-09 with total page 277 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book is designed to fill a professional vacuum in the new field of advance, high-angle, vectored stealth aircraft. The subject matter presented in the volume has never before been investigated and presented as a unified field of study because it covers entirely new fields and because specialized fragments of this unified field are scattered throughout literature in specific problems. The book is of interest to aeronautical and mechanical engineers, electrical and control engineers, aerospace industry, USAF, US Navy, NASA, pilots and instructors.
Download or read book Assessment of Aerodynamic Performance of V STOL and STOVL Fighter Aircraft written by and published by . This book was released on 1984 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Proceedings of High Speed Aerodynamics I written by Adriana Năstase and published by . This book was released on 1987 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book AGARD Index of Publications written by Organisation du traité de l'Atlantique Nord. Groupe consultatif pour la recherche et le développement aérospatial. Technical Information Panel and published by . This book was released on 1995 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering A Cumulative Index to the 1984 Issues of the Continuing Bibliography written by and published by . This book was released on 1985 with total page 582 pages. Available in PDF, EPUB and Kindle. Book excerpt:
