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Static Aerodynamic Characteristics Of A Scout Fin With An Enlarged Tip Control At Mach Numbers From 040 To 463
Download Static Aerodynamic Characteristics Of A Scout Fin With An Enlarged Tip Control At Mach Numbers From 040 To 463 full books in PDF, epub, and Kindle. Read online Static Aerodynamic Characteristics Of A Scout Fin With An Enlarged Tip Control At Mach Numbers From 040 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 Static Aerodynamic Characteristics of a Scout Fin with an Enlarged Tip Control at Mach Numbers from 0.40 to 4.63 by : Robert J. Keynton
Download or read book Static Aerodynamic Characteristics of a Scout Fin with an Enlarged Tip Control at Mach Numbers from 0.40 to 4.63 written by Robert J. Keynton and published by . This book was released on 1971 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of an experimental investigation to determine the static longitudinal aerodynamic characteristics of a fin with an enlarged tip control and the hinge-moment coefficients of the enlarged tip control. The model was tested at angles of attack from -6 [degree] to 6 [degree] and fin tip control deflections from -20° to 20°. A 1/8-scale model of the Scout first stage, with a tangent ogive nose, was used for these tests. Basic data obtained include the pitching-moment, rolling-moment, and normal-force coefficients of the fin and the hinge-moment coefficient of the enlarged tip control.
Book Synopsis Investigation of the Static Longitudinal Aerodynamic Characteristics of a 1/10-scale Model of the Blue Scout Jr. at Mach Numbers from 0.40 to 1.03 by : Thomas C. Kelly
Download or read book Investigation of the Static Longitudinal Aerodynamic Characteristics of a 1/10-scale Model of the Blue Scout Jr. at Mach Numbers from 0.40 to 1.03 written by Thomas C. Kelly and published by . This book was released on 1962 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Stability and Control Characteristics at Mach Numbers of 2.50, 3.00, and 3.71 of a Variable- Wing-sweep Configuration with Outboard Wing Panels Swept Back 75° by : Gerald V. Foster
Download or read book Stability and Control Characteristics at Mach Numbers of 2.50, 3.00, and 3.71 of a Variable- Wing-sweep Configuration with Outboard Wing Panels Swept Back 75° written by Gerald V. Foster and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of Wraparound Fins Mounted on Bodies of Revolution and Rheir Influence on the Missile Static Stability at Mach Numbers from 0.3 to 1.3 by : Calvin Wayne Dahlke
Download or read book Aerodynamic Characteristics of Wraparound Fins Mounted on Bodies of Revolution and Rheir Influence on the Missile Static Stability at Mach Numbers from 0.3 to 1.3 written by Calvin Wayne Dahlke and published by . This book was released on 1972 with total page 376 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental aerodynamic investigations were conducted for several wraparound fins and one planar fin configuration on bodies of revolution at Mach number ranging from 0.3 to 1.3 and angles of attack from -6 degrees to 6 degrees at 0 degrees at sideslip angle. Six component aerodynamic forces and moments were recorded on the complete missile configuration while simultaneously measuring the aerodynamic normal force and bending moments acting on each fin. The fin configuration parameters varied include chord length, fin thickness, leading edge configuration, tip chord geometry and body, root chord gap. The report presents the plotted coefficient data in two volumes. Volume I contains the complete missile aerodynamic data. Volume 2 contains the individual fin aerodynamic data.
Book Synopsis The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50° by : John B. McDevitt
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:
Book Synopsis Static Longitudinal Aerodynamic Characteristics at Transonic Speeds and Angles of Attack Up to 99° of a Reentry Glider Having Folding Wing-tip Panels by : Walter B. Olstad
Download or read book Static Longitudinal Aerodynamic Characteristics at Transonic Speeds and Angles of Attack Up to 99° of a Reentry Glider Having Folding Wing-tip Panels written by Walter B. Olstad and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Deflected Wing Tips on the Aerodynamic Characteristics of a Canard Configuration at Mach Numbers from 0.7 to 3.5 by : Victor L. Peterson
Download or read book Effects of Deflected Wing Tips on the Aerodynamic Characteristics of a Canard Configuration at Mach Numbers from 0.7 to 3.5 written by Victor L. Peterson and published by . This book was released on 1960 with total page 180 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 Characteristics of Thin Triangular Wings with Triangular-tip Control Surfaces at Supersonic Speeds with Mach Lines Behind the Leading Edge by : Warren A. Tucker
Download or read book Characteristics of Thin Triangular Wings with Triangular-tip Control Surfaces at Supersonic Speeds with Mach Lines Behind the Leading Edge written by Warren A. Tucker and published by . This book was released on 1948 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical analysis, based on the linearized equation for supersonic flow, of characteristics of triangular-tip control surfaces on thin triangular wings. By restriction to case for which Mach lines from wing apex lie behind the leading edge, a simplified treatment was possible; results of previous work on lift of triangular wings could be used to derive expressions for lift effectiveness, pitching moment, rolling-moment effectiveness, hinge moment due to control deflection, and hinge moment due to angle of attack. Comparisons were made with two-dimensional case.
Book Synopsis Static Aerodynamic Stability Characteristics of a Body of Revolution with Wraparound Fins at Mach Numbers from 1.6 to 2.86 by : John E. Vaughn
Download or read book Static Aerodynamic Stability Characteristics of a Body of Revolution with Wraparound Fins at Mach Numbers from 1.6 to 2.86 written by John E. Vaughn and published by . This book was released on 1972 with total page 322 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental aerodynamic investigations were conducted in the NASA Langley Unitary Plan wind tunnel for several wraparound fins with straight and with swept leading edge mounted on bodies of revolution. Mach number ranged from 1.6 to 2.86 while angle of attack was varied from -6 degrees to 6 degrees at 0 degrees sideslip angle. Six component aerodynamic force and moment data were recorded on the complete missile configuration while simultaneously recording the aerodynamic normal force and bending moments acting on each fin. The results of these tests are presented herein in plotted form. The number designation given the test is UPWT 980.
Book Synopsis Stability and Control Characteristics at a Mach Number of 2.01 of a Variable-wing-sweep Configuration with Outboard Wing Panels Swept Back 75° by : M. Leroy Spearman
Download or read book Stability and Control Characteristics at a Mach Number of 2.01 of a Variable-wing-sweep Configuration with Outboard Wing Panels Swept Back 75° written by M. Leroy Spearman and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Aerodynamic Stability Characteristics of a Body of Revolution with Wraparound Fins at Mach Numbers from 0.5 to 1.3 by : John E. Vaughn
Download or read book Static Aerodynamic Stability Characteristics of a Body of Revolution with Wraparound Fins at Mach Numbers from 0.5 to 1.3 written by John E. Vaughn and published by . This book was released on 1972 with total page 306 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental aerodynamic investigations were conducted in the AEDC-4T wind tunnel for several wraparound fins with straight and with swept leading edge mounted on bodies of revolution. Mach number ranged from 0.50 to 1.30 while angle of attack was varied from -6 degrees to 6 degrees at 0 degrees sideslip angle. Six component aerodynamic force and moment data were recorded on the complete missile configuration while simultaneously recording the aerodynamic normal force and bending moments acting on each fin. The results of these tests are presented in plotted form. (Author).
Book Synopsis The Effects of Wing Plan Form on the Static Longitudinal Aerodynamic Characteristics of a Flat-top Hypersonic Aircraft at Mach Numbers from 0.6 to 1.4 by : Stuart L. Treon
Download or read book The Effects of Wing Plan Form on the Static Longitudinal Aerodynamic Characteristics of a Flat-top Hypersonic Aircraft at Mach Numbers from 0.6 to 1.4 written by Stuart L. Treon and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length by : Carlton S. James
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.
Book Synopsis Aerodynamic Characteristics of Low Aspect Ratio Fins at Mach Numbers from 0.80 to 1.30 by : D.K. Smith
Download or read book Aerodynamic Characteristics of Low Aspect Ratio Fins at Mach Numbers from 0.80 to 1.30 written by D.K. Smith and published by . This book was released on 1971 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
