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Effects Of Size Of External Stores On The Aerodynamic Characteristics Of An Unswept And A 45 Degree Sweptback Wing Of Aspect Ratio 4 And A 60 Degree Delta Wing At Mach Numbers Of 141 162 And 196
Download Effects Of Size Of External Stores On The Aerodynamic Characteristics Of An Unswept And A 45 Degree Sweptback Wing Of Aspect Ratio 4 And A 60 Degree Delta Wing At Mach Numbers Of 141 162 And 196 full books in PDF, epub, and Kindle. Read online Effects Of Size Of External Stores On The Aerodynamic Characteristics Of An Unswept And A 45 Degree Sweptback Wing Of Aspect Ratio 4 And A 60 Degree Delta Wing At Mach Numbers Of 141 162 And 196 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 Size of External Stores on the Aerodynamic Characteristics of an Unswept and a 45 Degree Sweptback Wing of Aspect Ratio 4 and a 60 Degree Delta Wing at Mach Numbers of 1.41, 1.62, and 1.96 by : Carl R. Jacobsen
Download or read book Effects of Size of External Stores on the Aerodynamic Characteristics of an Unswept and a 45 Degree Sweptback Wing of Aspect Ratio 4 and a 60 Degree Delta Wing at Mach Numbers of 1.41, 1.62, and 1.96 written by Carl R. Jacobsen and published by . This book was released on 1953 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of the Spanwise, Chordwise, and Vertical Location of an External Store on the Aerodynamic Characteristics of a 45 Degree Sweptback Tapered Wing of Aspect Ratio 4 at Mach Numbers of 1.41, 1.62, and 1.96 by : Carl R. Jacobsen
Download or read book Effects of the Spanwise, Chordwise, and Vertical Location of an External Store on the Aerodynamic Characteristics of a 45 Degree Sweptback Tapered Wing of Aspect Ratio 4 at Mach Numbers of 1.41, 1.62, and 1.96 written by Carl R. Jacobsen and published by . This book was released on 1953 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Overhang Balance on the Hinge-moment and Effectiveness Characteristics of an Unswept Trailing-edge Control on a 60 Degree Delta Wing at Transonic and Supersonic Speeds by : Lawrence D. Guy
Download or read book Effects of Overhang Balance on the Hinge-moment and Effectiveness Characteristics of an Unswept Trailing-edge Control on a 60 Degree Delta Wing at Transonic and Supersonic Speeds written by Lawrence D. Guy and published by . This book was released on 1954 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation has been made of two unswept, partial-span, flap-type controls (differing only in hinge-line location) mounted on a 60 degree delta wing. One control was unbalanced and the other has a 100-percent overhang balance. Control hinge moments as well as aerodynamic characteristics of the complete wing-body combination were obtained for control deflections from 0 to 40 degrees over an angle-of-attack range of plus or minus 12 degrees at Mach numbers from 0.75 to 1.96. Reynolds numbers varied between 2,200,000 and 2,200,000. Expressions derived from linear theory for the hinge-moment coefficient due to angle of attack for unswept partial-span controls (which extend neither to the wing tip nor to the wing center line) on triangular wings having subsonic leading edges are given in an appendix.
Book Synopsis Effects of Systematically Varying the Spanwise and Vertical Location of an External Store on the Aerodynamic Characteristics of an Unswept Tapered Wing of Aspect Ratio 4 at Mach Numbers of 1.41, 1.62, and 1.96 by : Carl R. Jacobsen
Download or read book Effects of Systematically Varying the Spanwise and Vertical Location of an External Store on the Aerodynamic Characteristics of an Unswept Tapered Wing of Aspect Ratio 4 at Mach Numbers of 1.41, 1.62, and 1.96 written by Carl R. Jacobsen and published by . This book was released on 1952 with total page 34 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 An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence by : John A. Axelson
Download or read book An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence written by John A. Axelson and published by . This book was released on 1948 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability.
Book Synopsis Effects of External Stores on the Static Longitudinal Aerodynamic Characteristics of a Model of a 45 Degree Swept-wing Fighter Airplane at Mach Numbers of 1.61 and 2.01 by : Gerald V. Foster
Download or read book Effects of External Stores on the Static Longitudinal Aerodynamic Characteristics of a Model of a 45 Degree Swept-wing Fighter Airplane at Mach Numbers of 1.61 and 2.01 written by Gerald V. Foster and published by . This book was released on 1956 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of various external-store configurations of the longitudinal and lateral aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane. Pylon-mounted stores located at 23.8, 46.2, and 67.0 percent of the wing semispan were tested individually and in various combinations. The inboard stores relative to outboard stores were similar in shape but approximately 25 percent greater in size. The stores located at 46.2 percent of the wing semispan represented a large fuel tank and had an unsymmetrical shape.
Book Synopsis Effect of an End Plate on the Aerodynamic Characteristics of a 20.55 Degree Sweptback Wing with an Aspect Ratio of 2.67 and a Taper Ratio of 0.5 by : James M. Watson
Download or read book Effect of an End Plate on the Aerodynamic Characteristics of a 20.55 Degree Sweptback Wing with an Aspect Ratio of 2.67 and a Taper Ratio of 0.5 written by James M. Watson and published by . This book was released on 1950 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation by the transonic-bump method conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effect of an end plate on the aerodynamic characteristics of a 20.55 degree sweptback wing with an aspect ratio of 2.67 and a taper ratio of 0.5 indicated that the end plate affect the aerodynamic characteristics of the wing at transonic Mach numbers in the same manner as has been observed for swept and unswept wings at low speeds.
Book Synopsis Aerodynamic Loads on an External Store Adjacent to a 45 Degree Sweptback Wing at Mach Numbers from 0.70 to 1.96, Including an Evaluation of Techniques Used by : Lawrence D. Guy
Download or read book Aerodynamic Loads on an External Store Adjacent to a 45 Degree Sweptback Wing at Mach Numbers from 0.70 to 1.96, Including an Evaluation of Techniques Used written by Lawrence D. Guy and published by . This book was released on 1955 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic forces and moments have been obtained in the Langley 9- by 12-inch blowdown tunnel on an external store and on a 45 degree swept-back wing-body combination measured separately at Mach numbers from 0.70 to 1.96. The wing was cantilevered and had an aspect ratio of 4.0; the store was independently sting-mounted and had a Douglas Aircraft Co. (DAC) store shape. The angle of attack range was from -3 degrees to 12 degrees and the Reynolds number (based on wing mean aerodynamic chord) varied from 1.2 x10(6) to 1.7 x 10(6). Wing-body transonic forces and moments have been compared with data of a geometrically similar full-scale model tested in the Langley 16-foot and 8-foot transonic tunnels in order to aid in the evaluation of transonic-tunnel interference.
Book Synopsis Effects of the Spanwise, Chordwise, and Vertical Location of an External Store on the Aerodynamic Characteristics of a 60 Degree Delta Wing at Mach Numbers of 1.41, 1.62, and 1.96 by : Carl R. Jacobsen
Download or read book Effects of the Spanwise, Chordwise, and Vertical Location of an External Store on the Aerodynamic Characteristics of a 60 Degree Delta Wing at Mach Numbers of 1.41, 1.62, and 1.96 written by Carl R. Jacobsen and published by . This book was released on 1952 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 by : Kenneth P. Spreemann
Download or read book Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of a 40 Degree Swept Back Wing of Aspect Ratio 4.5 by : P. S. Barna
Download or read book Aerodynamic Characteristics of a 40 Degree Swept Back Wing of Aspect Ratio 4.5 written by P. S. Barna and published by . This book was released on 1957 with total page 5 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Some Wing Variations Including Wingtip Deflection on the Static Longitudinal Aerodynamic Characteristics of a Delta-wing Configuration at Supersonic Speeds by :
Download or read book Effects of Some Wing Variations Including Wingtip Deflection on the Static Longitudinal Aerodynamic Characteristics of a Delta-wing Configuration at Supersonic Speeds written by and published by . This book was released on 1960 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Aspect Ratio on Air Flow at a High Subsonic Mach Numbers by : W. F. Lindsey
Download or read book Effects of Aspect Ratio on Air Flow at a High Subsonic Mach Numbers written by W. F. Lindsey and published by . This book was released on 1948 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to two on the air flow past a wing at high subsonic Mach numbers. The results indicated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation.
Book Synopsis The Effect of Leading-edge Droop Upon the Pressure Distribution and Aerodynamic Loading Characteristics of a 45 Degree Sweptback Wing at Transonic Speeds by : James W. Schmeer
Download or read book The Effect of Leading-edge Droop Upon the Pressure Distribution and Aerodynamic Loading Characteristics of a 45 Degree Sweptback Wing at Transonic Speeds written by James W. Schmeer and published by . This book was released on 1955 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The leading edge of the wing was drooped 6 degrees about the 19-percent chord line from 0.15 semispan to the wing tip. Data were obtained at Mach numbers of 0.80 to 1.03 with average Reynolds numbers of 5,700,000 to 6,300,000, respectively. The results of this investigation are compared with the pressure data obtained with the undrooped or basic wing of a previous investigation.
