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Download Static Stability Characteristics Of A Delta Winged Airplane Configuration With Nacelles A Trapezoidal Canard And A Drooped Tail At Mach Numbers From 070 To 352 full books in PDF, epub, and Kindle. Read online Static Stability Characteristics Of A Delta Winged Airplane Configuration With Nacelles A Trapezoidal Canard And A Drooped Tail At Mach Numbers From 070 To 352 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author :
Publisher :
ISBN 13 :
Total Pages : 1466 pages
Book Rating : 4.3/5 (126 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1966 with total page 1466 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Edward C. Polhamus
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.3/5 (91 download)
Download or read book Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical-tail-load Characteristics of a Complete Model Having a Delta Wing written by Edward C. Polhamus and published by . This book was released on 1958 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation at high subsonic speeds has been conducted to determine the effect of fuselage forebody strakes on the static stability and the vertical-tail-load characteristics of an airplane-type configuration having a delta wing. The tests were made at Mach numbers from 0.60 to 0.92 corresponding to Reynolds numbers from 3,000,000 to 4,200,000, based on the wing mean aerodynamic chord, and at angles of attack from approximately -2 to 24 degrees.
Author : William R. Bates
Publisher :
ISBN 13 :
Total Pages : 38 pages
Book Rating : 4.3/5 (91 download)
Download or read book Low-speed Static Lateral Stability Characteristics of a Canard Model Having a 60© Triangular Wing and Horizontal Tail written by William R. Bates and published by . This book was released on 1949 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John M. Riebe
Publisher :
ISBN 13 :
Total Pages : 32 pages
Book Rating : 4.3/5 (91 download)
Download or read book Low-speed Static Stability Characteristics of a Cambered-delta-wing Model written by John M. Riebe and published by . This book was released on 1956 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the static stability characteristics of a cambered-delta-wing model. The cambered delta wing was derived from a segment of a cone selected so that the projected plan form with a wing dihedral angle of zero degrees was the same as a 60 degree delta wing. The projected plan form had an aspect ratio of 2.31.
Author : Powell M. Lovell
Publisher :
ISBN 13 :
Total Pages : 42 pages
Book Rating : 4.3/5 (91 download)
Download or read book Effects of Wing Position and Vertical-tail Configuration on Stability and Control Characteristics of a Jet-powered Delta-wing Vertically Rising Airplane Model written by Powell M. Lovell and published by . This book was released on 1957 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted to determine the effects of wing position and vertical tail configuration on the stability and control characteristics of a jet-powered delta-wing vertically rising airplane model. A ducted-fan powerplant was used because there was no hot-jet powerplant of sufficiently small size and adequate reliability available. In addition to conventional flap-type control surfaces on the wings and vertical tails, the model had jet-reaction controls provided by movable eyelids at the rear of the tail pipe and by air bled from the main duct and exhausted through movable nozzles near the wing tips. The investigation consisted of flight and force tests of three model configurations: a high wing with a top-mounted vertical tail, a high wing with top- and bottom-mounted vertical tails, and a low wing with the top-mounted vertical tail. The flight tests, which were made in the Langley full-scale tunnel, represented slow constant-altitude transitions from hovering to normal unstalled forward flight.
Author : Robert S. Osborne
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.:/5 (31 download)
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 written by Robert S. Osborne and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Frank L. Clark
Publisher :
ISBN 13 :
Total Pages : 74 pages
Book Rating : 4.3/5 (91 download)
Download or read book An Investigation at Mach Numbers 1.94 and 2.41 of Jet Effects Upon the Longitudinal and Directional Stability of a General Aircraft Configuration Employing Wing-tip-mounted Nacelles written by Frank L. Clark and published by . This book was released on 1958 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : M. Leroy Spearman
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
Download or read book Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.01 of a Tailless Delta V/STOL Configuration Having Variable-sweep Wing Panels written by M. Leroy Spearman and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Alex Goodman
Publisher :
ISBN 13 :
Total Pages : 82 pages
Book Rating : 4.3/5 (91 download)
Download or read book Effects of Wing Position and Fuselage Size on the Low-speed Static and Rolling Stability Characteristics of a Delta-wing Model written by Alex Goodman and published by . This book was released on 1954 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made to determine the effects of wing position and fuselage size on the low-speed static and rolling stability characterististics of airplane models having a triangular wing and vertical tail surfaces.
Author : Jim A. Penland
Publisher :
ISBN 13 :
Total Pages : 34 pages
Book Rating : 4.3/5 (91 download)
Download or read book Lift, Drag, and Static Longitudinal Stability Data from an Exploratory Investigation at a Mach Number of 6.86 of an Airplane Configuration Having a Wing of Trapezoidal Plan Form written by Jim A. Penland and published by . This book was released on 1955 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Carlton S. James
Publisher :
ISBN 13 :
Total Pages : 42 pages
Book Rating : 4.:/5 (317 download)
Download or read book Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length written by Carlton S. James and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: An aircraft configuration, previously conceived as a means to achieve favorable aerodynamic stability characteristics., high lift-drag ratio, and low heating rates at high supersonic speeds., was modified in an attempt to increase further the lift-drag ratio without adversely affecting the other desirable characteristics. The original configuration consisted of three identical triangular wing panels symmetrically disposed about an ogive-cylinder body equal in length to the root chord of the panels. This configuration was modified by altering the angular disposition of the wing panels, by reducing the area of the panel forming the vertical fin, and by reshaping the body to produce interference lift. Six-component force and moment tests of the modified configuration at combined angles of attack and sideslip were made at a Mach number of 3.3 and a Reynolds number of 5.46 million. A maximum lift-drag ratio of 6.65 (excluding base drag) was measured at a lift coefficient of 0.100 and an angle of attack of 3.60. The lift-drag ratio remained greater than 3 up to lift coefficient of 0.35. Performance estimates, which predicted a maximum lift-drag ratio for the modified configuration 27 percent greater than that of the original configuration, agreed well with experiment. The modified configuration exhibited favorable static stability characteristics within the test range. Longitudinal and directional centers of pressure were slightly aft of the respective centroids of projected plan-form and side area.
Author : Samuel M. Dollyhigh
Publisher :
ISBN 13 :
Total Pages : 126 pages
Book Rating : 4.:/5 (31 download)
Download or read book Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86 written by Samuel M. Dollyhigh and published by . This book was released on 1971 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60 deg leading-edge-sweep wing; however, a small amount of data were obtained for a 44 deg leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard. Further, this interference decreased somewhat with increasing Mach number. Raising the canard above the plane of the wing also greatly decreased the interference of the canard deflection on the wing lift. However, at Mach 2.86 the presence of the canard in the high position had a greater unfavorable interference effect at high angles of attack than the canard in the wing plane. This interference resulted in the in-plane canard having better trimmed performance at Mach 2.86 for the same center-of-gravity location.
Author : William C. Sleeman
Publisher :
ISBN 13 :
Total Pages : 34 pages
Book Rating : 4.3/5 (91 download)
Download or read book Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Author : Edward Charles Polhamus
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
Download or read book Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical-tail-load Characteristics of a Complete Model Having a Delta Wing written by Edward Charles Polhamus and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Dennis E. Fuller
Publisher :
ISBN 13 :
Total Pages : 122 pages
Book Rating : 4.:/5 (31 download)
Download or read book Static Stability Characteristics at Mach Numbers from 1.90 to 4.63 of a 76° Swept Arrow Wing Model with Variations in Horizontal-tail Height, Wing Height, and Dihedral written by Dennis E. Fuller and published by . This book was released on 1967 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Charles F. Whitcomb
Publisher :
ISBN 13 :
Total Pages : 34 pages
Book Rating : 4.3/5 (91 download)
Download or read book Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches written by Charles F. Whitcomb and published by . This book was released on 1956 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
Author : John B. McDevitt
Publisher :
ISBN 13 :
Total Pages : 114 pages
Book Rating : 4.:/5 (31 download)
Download or read book The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50° written by John B. McDevitt and published by . This book was released on 1960 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
