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Aerodynamic Characteristics Of The Hast Missile At Mach Numbers 225 30 And 40
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Book Synopsis Aerodynamic Characteristics of the HAST Missile at Mach Numbers 2.25, 3.0, and 4.0 by : J. H. Jones
Download or read book Aerodynamic Characteristics of the HAST Missile at Mach Numbers 2.25, 3.0, and 4.0 written by J. H. Jones and published by . This book was released on 1972 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static-force tests were conducted at Mach number 2.25, 3, and 4 on a 0.25 -scale model of the Beech High Altitude Supersonic Target (HAST) missile.
Book Synopsis Static Stability and Drag Characteristics of the HAST Missile at Mach Numbers 2.25, 3.0, and 4.0 by : J. T. Best (Jr.)
Download or read book Static Stability and Drag Characteristics of the HAST Missile at Mach Numbers 2.25, 3.0, and 4.0 written by J. T. Best (Jr.) and published by . This book was released on 1974 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static-force tests were conducted at Mach number 2.25, 3, and 4 on a 0.25 -scale model of the High Altitude Supersonic Target (HAST) missile.
Book Synopsis Aerodynamic Characteristics of the HAST Missile at Mach Numbers 2.25, 3.0, and 4.0 by : J. H. Jones
Download or read book Aerodynamic Characteristics of the HAST Missile at Mach Numbers 2.25, 3.0, and 4.0 written by J. H. Jones and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static-force tests were conducted at Mach number 2.25, 3, and 4 on a 0.25 -scale model of the Beech High Altitude Supersonic Target (HAST) missile.
Book Synopsis Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.16 of a Blunt-nose Missile Model Having a Triangular Cross Section and Fixed Triform Fins by : William J. Monta
Download or read book Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.16 of a Blunt-nose Missile Model Having a Triangular Cross Section and Fixed Triform Fins written by William J. Monta and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics at Mach Numbers from 1.50 to 4.63 of a Maneuverable Missile with In-line Cruciform Wings and Canard Surfaces by : M. Leroy Spearman
Download or read book Aerodynamic Characteristics at Mach Numbers from 1.50 to 4.63 of a Maneuverable Missile with In-line Cruciform Wings and Canard Surfaces written by M. Leroy Spearman and published by . This book was released on 1967 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley Unitary Plan wind tunnel at Mach numbers from 1.50 to 4.63 to determine the aerodynamic characteristics of a maneuverable missile having in-line cruciform wings and canard surfaces oriented in 45° roll planes.
Book Synopsis Longitudinal Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.86 for a Fixed-span Missile with Three Wing Planforms by : M. Leroy Spearman
Download or read book Longitudinal Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.86 for a Fixed-span Missile with Three Wing Planforms written by M. Leroy Spearman and published by . This book was released on 1977 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics at Mach Numbers of 3.95 and 4.63 for a Missile Model Having All-movable Wings and Interdigitated Tails by :
Download or read book Aerodynamic Characteristics at Mach Numbers of 3.95 and 4.63 for a Missile Model Having All-movable Wings and Interdigitated Tails written by and published by . This book was released on 1967 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics at Mach Numbers from 0.40 to 2.86 of a Missile Model Having All Movable Wings and Interdigitated Tails by :
Download or read book Aerodynamic Characteristics at Mach Numbers from 0.40 to 2.86 of a Missile Model Having All Movable Wings and Interdigitated Tails written by and published by . This book was released on 1965 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic and Inlet Characteristics of the HAST I and II Missiles at Mach Numbers 0.5 to 1.6 by :
Download or read book Aerodynamic and Inlet Characteristics of the HAST I and II Missiles at Mach Numbers 0.5 to 1.6 written by and published by . This book was released on 1974 with total page 113 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic and inlet characteristics were investigated for 0.I5- scale models of the HAST I and II missiles. Mach number was varied from 0.5 to 1.6 for the HAST I test phase, but the HAST II models were tested only at Mach number 1.6. Reynolds number based on model length, varied between 13.9 and 18.7 million. Data were obtained on the HAST I for canard deflection angles from -20 to 20 deg, aileron deflection angles from 0 to 10 deg, inlet capture area ratios from 0 to 1.2, angles of attack from -4 to 12 deg, and sideslip angles of 0 to 6 deg. Data were obtained on the HAST II at angles of attack from -4 to 4 deg with canard deflection angle, aileron deflection angle, and sideslip angle all zero. Also characteristics of 18 HAST I and six HAST II configurations were evaluated. Test results indicated that canard deflection significantly affected axial- force, pitching-moment, and trim characteristics while aileron deflection affected only the rolling-moment characteristics. The inlet performance parameters showed significant variation with changes in capture area ratio and free-stream Mach number.
Book Synopsis Longitudinal Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.86 for a Spanmissile with Three Wing Planforms by : M. Leroy Spearman
Download or read book Longitudinal Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.86 for a Spanmissile with Three Wing Planforms written by M. Leroy Spearman and published by . This book was released on 1977 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Longitudinal Aerodynamic Characteristics of Five Hypersonic Missile Configurations at Mach Numbers from 2.01 to 6.01 by : George C. Jr Ashby
Download or read book Longitudinal Aerodynamic Characteristics of Five Hypersonic Missile Configurations at Mach Numbers from 2.01 to 6.01 written by George C. Jr Ashby and published by . This book was released on 1961 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of a Canard-controlled Missile at Mach Numbers of 1.5 and 2.0 by : Donald L. Kassner
Download or read book Aerodynamic Characteristics of a Canard-controlled Missile at Mach Numbers of 1.5 and 2.0 written by Donald L. Kassner and published by . This book was released on 1977 with total page 296 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722067939 Total Pages :32 pages Book Rating :4.0/5 (679 download)
Book Synopsis An Experimental and Theoretical Study of the Aerodynamic Characteristics of Some Generic Missile Concepts at Mach Numbers from 2 To 6. 8 by : National Aeronautics and Space Administration (NASA)
Download or read book An Experimental and Theoretical Study of the Aerodynamic Characteristics of Some Generic Missile Concepts at Mach Numbers from 2 To 6. 8 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-30 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study has been made of the experimental and theoretical aerodynamic characteristics for some generic high-speed missile concepts at Mach numbers from 2 to 6.8. The basic body for this study had a length-to-diameter ratio of 10 with the forward half being a modified blunted ogive and the rear half being a cylinder. Modifications made to the basic body included the addition of an after body flare, the addition of highly swept cruciform wings and the addition of highly swept aft tails. The effects of some controls were also investigated with all-moving wing controls on the flared body and trailing-edge flap controls on the winged body. The results indicated that the addition of a flare, wings, or tails to the basic body all provided static longitudinal stability with varying amounts of increased axial force. The control arrangements were effective in producing increments of normal-force and pitching-moment at the lower Mach numbers. At the highest Mach number, the flap control on the winged body was ineffective in producing normal-force or pitching-moment but the all-moving wing control on the flared body, while losing pitch effectiveness, still provided normal-force increments. Calculated results obtained through the use of hypersonic impact theory were in generally good agreement with experiment at the higher Mach numbers but were not accurate at the lower Mach numbers. Spearman, M. Leroy and Braswell, Dorothy O. Langley Research Center RTOP 505-69-20-01...
Book Synopsis An Experimental and Theoretical Study of the Aerodynamic Characteristics of Some Generic Missile Concepts at Mach Numbers from 2 to 6.8 by :
Download or read book An Experimental and Theoretical Study of the Aerodynamic Characteristics of Some Generic Missile Concepts at Mach Numbers from 2 to 6.8 written by and published by . This book was released on 1994 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Stability and Drag Characteristics of the HAST Missile at Mach Numbers 2.25, 3.0, and 4.0 by : J. T. Best (Jr.)
Download or read book Static Stability and Drag Characteristics of the HAST Missile at Mach Numbers 2.25, 3.0, and 4.0 written by J. T. Best (Jr.) and published by . This book was released on 1974 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static-force tests were conducted at Mach number 2.25, 3, and 4 on a 0.25 -scale model of the High Altitude Supersonic Target (HAST) missile.
Book Synopsis Aerodynamic Characteristics of a Swept-wing Cruise Missile at Mach Numbers from 0.50 to 2.86 by : M. Leroy Spearman
Download or read book Aerodynamic Characteristics of a Swept-wing Cruise Missile at Mach Numbers from 0.50 to 2.86 written by M. Leroy Spearman and published by . This book was released on 1972 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis High Angle of Attack Missile Aerodynamics at Mach Numbers 0.30 to 1.5 by :
Download or read book High Angle of Attack Missile Aerodynamics at Mach Numbers 0.30 to 1.5 written by and published by . This book was released on 1980 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt: A large body of wind tunnel data was generated by tests of a smooth missile model with several interchangeable nose parts. The tests were conducted at subsonic through supersonic speeds at angles of attack from 0 to 180 degrees. They were part of the FDL and SAMSO technology studies which preceded design of the MX missile. Measurements of both surface pressures and total forces and moments were made at a variety of Mach numbers and Reynolds number combinations. This data was supplemented with wake flow-field measurements of the impact pressure and flow direction at angles of attack where maximum induced side force was expected to occur. A review of the literature for subsonic and transonic aerodynamic characteristics of bodies of revolution was conducted. A comprehensive discussion is provided of the important variables of the high angle of attack flow phenomena. The test data provided insight into the effect of several variables that had not been adequately treated in the past. The high angle of attack data was analyzed to deduce the vortex shedding location, the vortex strength, and the vortex paths in the wake. Discrete vortex theory was examined as a method which could be modified, based on experimental data, and used to predict the aerodynamic characteristics of missiles to greater accuracy. An alternate approach to developing a prediction method was explored by means of a correlation of the surface pressure data.
