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Effects Of Wing Planform On The Aerodynamic Characteristics Of A Wing Body Tail Model At Mach Numbers From 170 To 463
Download Effects Of Wing Planform On The Aerodynamic Characteristics Of A Wing Body Tail Model At Mach Numbers From 170 To 463 full books in PDF, epub, and Kindle. Read online Effects Of Wing Planform On The Aerodynamic Characteristics Of A Wing Body Tail Model At Mach Numbers From 170 To 463 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 by : Royce L. McKinney
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 written by Royce L. McKinney and published by . This book was released on 1965 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers from 1.70 to 4.63 by : Lloyd S. Jernell
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers from 1.70 to 4.63 written by Lloyd S. Jernell and published by . This book was released on 1965 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Effects of Tail Height and Wing Plan Form on the Static Longitudinal Stability Characteristics of a Small-scale Model at High Subsonic Speeds by : Albert G. Few
Download or read book Some Effects of Tail Height and Wing Plan Form on the Static Longitudinal Stability Characteristics of a Small-scale Model at High Subsonic Speeds written by Albert G. Few and published by . This book was released on 1954 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.
Book Synopsis Effect of Wing Leading-edge Shape on Aerodynamic Characteristics of a 67 ̊swept Wing-body Model at Mach 1.50 to 4.63 by : Robert G. Kyle
Download or read book Effect of Wing Leading-edge Shape on Aerodynamic Characteristics of a 67 ̊swept Wing-body Model at Mach 1.50 to 4.63 written by Robert G. Kyle and published by . This book was released on 1966 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations by : Harry W. Carlson
Download or read book An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations written by Harry W. Carlson and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: An experimental investigation has been performed to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and given longitudinal distribution of cross-sectional area but various cross-section shapes were tested at a Mach number of 2.01. The bodies were tested alone and in combination with a 47° sweptback wing having a 6-percent-thick hexagonal section.
Book Synopsis Effects of Wing Dihedral and Planform on Stability Characteristics of a Research Model at Mach Numbers from 1.80 to 4.63 by : Maurice O. Feryn
Download or read book Effects of Wing Dihedral and Planform on Stability Characteristics of a Research Model at Mach Numbers from 1.80 to 4.63 written by Maurice O. Feryn and published by . This book was released on 1965 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches by : Charles F. Whitcomb
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.
Book Synopsis Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 by : Marlowe D. Cassetti
Download or read book Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 written by Marlowe D. Cassetti and published by . This book was released on 1961 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Book Synopsis Aerodynamic Characteristics of Several Cranked Leading-edge Wing-body Combinations at Mach Numbers from 0.4 to 2.94 by : Edward J. Hopkins
Download or read book Aerodynamic Characteristics of Several Cranked Leading-edge Wing-body Combinations at Mach Numbers from 0.4 to 2.94 written by Edward J. Hopkins and published by . This book was released on 1967 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 by : Howard F. Savage
Download or read book The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 written by Howard F. Savage and published by . This book was released on 1957 with total page 662 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
Book Synopsis Effects of External Stores on the Aerodynamic Characteristics of a 60 Deg Delta-wing Fighter Model at Mach 1.60 to 2.87 by :
Download or read book Effects of External Stores on the Aerodynamic Characteristics of a 60 Deg Delta-wing Fighter Model at Mach 1.60 to 2.87 written by and published by . This book was released on 1977 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Review of the Planform Effects on the Low-speed Aerodynamic Characteristics of Triangular and Modified Triangular Wings by : Kenneth Razak
Download or read book A Review of the Planform Effects on the Low-speed Aerodynamic Characteristics of Triangular and Modified Triangular Wings written by Kenneth Razak and published by . This book was released on 1966 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Longitudinal Aerodynamic Characteristics of a Fighter-type Airplane Model with a Low-aspect-ratio Unswept Wing and Tee-tail by : Gerald Hieser
Download or read book Transonic Longitudinal Aerodynamic Characteristics of a Fighter-type Airplane Model with a Low-aspect-ratio Unswept Wing and Tee-tail written by Gerald Hieser and published by . This book was released on 1956 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 by : Earl D. Knechtel
Download or read book Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 written by Earl D. Knechtel and published by . This book was released on 1957 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to determine the effects of wing-tip droop on the longitudinal stability characteristics of a 53 and a 63 degree sweptback wing-body combination. Both models were tested with flat and abruptly drooped wing tips. The 63 degree wing was also tested with a curved drooped tip. In addition, the combined effects of wing fences and extended leading-edge flaps were investigated. The results showed that abrupt droop of the outer 40 percent of the basic 53 degree wing improved the stability characteristics of the model. For the 63 degree swept wing, curved droop caused slight beneficial effects on the stability, whereas abrupt droop caused adverse effects. In general, the most favorable stability characteristics were obtained for either flat or abruptly drooped wings with fences and extended leading-edge flaps.
Book Synopsis Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86 by : Samuel M. Dollyhigh
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.
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