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.
Download or read book Aerodynamic Characteristics of Wraparound Fins Mounted on Bodies of Revolution and Their Influence on the Missile Static Stability at Mach Numbers from 0 3 to 1 3 Volume II written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: OL-2AMCDR-1001-Vol-2See also Volume 1, AD-772 669.*Guided missiles, *Fins, Tube launched, Aerodynamic forces, Pitch(Motion), Roll, Yaw, Angle of attackWraparound finsExperimental 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 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 2 contains the individual fin aerodynamic data. (Modified author abstract).
Download or read book Aerodynamic Characteristics of Wraparound Fins Mounted on Bodies of Revolution and Their Influence on the Missile Static Stability at Mach Numbers from 0 3 to 1 3 Volume I written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: AMCDR-1001-Vol-1See also Volume 2, AD-772 670.*Guided missiles, *Fins, Tube launched, Aerodynamic forces, Pitch(Motion), Roll, Yaw, Angle of attackWraparound finsExperimental 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. (Modified author abstract).
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).
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 606 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.
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.
Download or read book Static Aerodynamic Stability Characteristics of Bodies 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 316 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wayne ;Craft, J. C. ;RD-TM-72-14AMCDR-1009*Guided missiles, *Fins, Aerodynamic stability, Aerodynamic forces, Pitch(Motion), Roll, Yaw, Angle of attackExperimental 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. (Author).
Download or read book A Summary of Aerodynamic Characteristics for Wrap around Fins from Mach 0 3 to 3 0 written by James A. Humphrey and published by . This book was released on 1977 with total page 234 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wrap-around fin effectiveness for tube-launched missiles was investigated in a series of 6 wind tunnel tests. Wind tunnels were AEDC Propulsion Wind Tunnel, NASA/Langley Research Center Unitary Plan Wind Tunnel and McDonnell Douglas 4-foot Trisonic Wind Tunnel. Mach number range was 0.3 to 3.0. Basic model was a 2-caliber secant ogive nose with an 8-caliber cylindrical afterbody and 21 fin configurations. Variations in the coefficients are presented for changes in fin geometry including taper ratio and leading edge sweep angle, aspect ratio, exposed semi-span, and root chord length; opening angle, fully closed to 10 deg past fully open; and body step down.
Download or read book Effects of Body and Fin Deflections on the Aerodynamic Characteristics in Pitch of a 0 065 scale Model of a Four stage Rocket Configuration at Mach Numbers of 1 41 and 1 82 written by Ross B. Robinson and published by . This book was released on 1959 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Aerodynamic Characteristics of Wrap around Fins at Mach Numbers of 0 3 to 3 0 written by C. Wayne Dahlke and published by . This book was released on 1976 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of investigations into many of the geometric and flow parameters influencing the aerodynamics of wrap-around fins are presented in this report. Particular emphasis is placed on defining static and dynamic roll characteristics between Mach numbers of 0.3 to 3.0. Among the geometric parameters highlighted are fin span, aspect ratio, leading edge sweep, leading edge shape, fin opening angle, and afterbody geometry. Comparisons of static stability, dynamic stability, and drag are made between the flat and the wrap- around fin. Problems associated with measurement of wrap-around fin rolling mounts are also discussed. An overview of the wrap-around fin roll moment characteristics are presented as an aid for making estimates and establishing testing techniques. This report supercedes RD-73-17.
Download or read book Some Effects of Fin Plan Form on the Static Stability of Fin body Combinations at Mach Number 4 06 written by Edward F. Ulmann and published by . This book was released on 1952 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Summary of Jet Plume Effects on the Stability Characteristics of a Body of Revolution with Various Fin Configurations at Mach Numbers from 0 2 to 2 3 written by George Batiuk and published by . This book was released on 1976 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report summarizes the studies made to date by the Army Missile Command on the effects of the rocket jet plume on the Stability characteristics of a body of revolution with various fin configurations and at various fin positions on the body. The Mach numbers ranged from 0.2 to 2.3. A normal jet plume simulator was used to obtain the desired plume effects. This report concerns itself with those tests conducted on a 5-in. diameter, 52-in. long model, with a 3 caliber tangent ogive nose.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1977 with total page 1118 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effect of Wrap around Fins on Aerodynamic Stability and Rolling Moment Variations written by C. W. Dahlke and published by . This book was released on 1973 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0 7 to 1 4 written by Calvin Wayne Dahlke and published by . This book was released on 1977 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a wind tunnel test, simulating rocket motor exhaust jet effects on missile aerodynamic at Mach numbers of 0.7 to 1.4 are presented. A normal jet plume simulator was used to induce afterbody boundary layer separation. Flow visualization techniques including both shadowgraph and oil flow photographs were taken. The primary emphasis for this report is the force and moment measurements taken on twelve configurations including: five tail fin configurations; body alone; three forward fin configurations; body flare combination; and two combinations of forward fins/strakes with tail fins. All force and moment coefficients are presented in plotted form. One configuration is shown with ground plane interference simulation. (Author).
Download or read book Aerodynamic Characteristics of Two Bodies of Revolution with Noses of Varying Spherical Bluntness at Mach Numbers from 0 6 to 1 5 written by E. G Allee (Jr) and published by . This book was released on 1973 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel investigation was conducted to determine the static stability characteristics of two bodies of revolution fitted with 2-, 3-, and 4-cal tangent ogive noses of varying spherical bluntness. Testing was conducted at Mach numbers from 0.6 to 1.5 and angles of attack from -2 to 14 deg. The major effect of blunting the noses was evidenced in the axial-force coefficient. Lengthening the noses from 2 to 4 cal caused a forward movement of the center-of-pressure location and a corresponding decrease in axial-force coefficient at Mach numbers of 1.0 and higher. Changing from a 5- to a 9-cal midbody resulted in an increase in axial-force coefficient and an aft movement of the center-of-pressure location. (Author).
Download or read book Collection of Technical Papers on Atmospheric Flight Mechanics written by and published by . This book was released on 1974 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt:
