Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Normal Force Center Of Pressure And Zero Lift Drag Of Several Ballistic Type Missiles At Mach Numbers Of 405
Download Normal Force Center Of Pressure And Zero Lift Drag Of Several Ballistic Type Missiles At Mach Numbers Of 405 full books in PDF, epub, and Kindle. Read online Normal Force Center Of Pressure And Zero Lift Drag Of Several Ballistic Type Missiles At Mach Numbers Of 405 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Normal Force, Center of Pressure, and Zero-lift Drag of Several Ballistic-type Missiles at Mach Numbers of 4.05 by : Edward F. Ulmann
Download or read book Normal Force, Center of Pressure, and Zero-lift Drag of Several Ballistic-type Missiles at Mach Numbers of 4.05 written by Edward F. Ulmann and published by . This book was released on 1954 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted at Mach number 4.05 to determine the aerodynamic characteristics of several missile models having turbulent boundary layers and to compare these results with available method of predicting the aerodynamic characteristics. (The condition of the boundary layer was determined by the china-clay-lacquer boundary-layer-visualization technique.) Normal force and pitching moment were measured through an angle-of-attack range of 0 to between 4 and 8 degrees, depending upon balance limitations, and at roll angles of 0 and 45 degrees; drag was measured only at 0 degrees angle of attack.
Book Synopsis Free-flight Investigation at Mach Numbers Between 0.5 and 1.7 of the Zero-lift Rolling Effectiveness and Drag of Various Surface, Spoiler, and Jet Controls on an 80° Delta-wing Missile by : Eugene D. Schult
Download or read book Free-flight Investigation at Mach Numbers Between 0.5 and 1.7 of the Zero-lift Rolling Effectiveness and Drag of Various Surface, Spoiler, and Jet Controls on an 80° Delta-wing Missile written by Eugene D. Schult and published by . This book was released on 1960 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Force Tests of Standard Hypervelocity Ballistic Models HB-1 and HB-2 at Mach 1.5 to 10 by : J. Don Gray
Download or read book Force Tests of Standard Hypervelocity Ballistic Models HB-1 and HB-2 at Mach 1.5 to 10 written by J. Don Gray and published by . This book was released on 1963 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of two standard, hypervelocity, ballistic-type models, designated HB-1 and HB-2 were investigated in the supersonic and hypersonic regimes. The tests were conducted at nominal Mach numbers of 1.5, 2, 3, 4, 5, 8, and 10 at Reynolds numbers from 0.07 to 2.55 x 10 to the 6th power, based on body diameter, and through an angle-of-attack range from -2 to 15 deg. The effects of Mach number, Reynolds number, and model attitude on the static stability and axial-force characteristics of the two configurations were investigated. The zero-lift, forebody, axial-force coefficient, CA, for both configurations was found to be sensitive to Reynolds number variations; whereas the initial normal-force curve slope, CN alpha, and center of-pressure, xcp/l, for only the flared-tail model (HB-2) were dependent upon the Reynolds number. (Author).
Book Synopsis An Improved Semiempirical Method for Calculating Aerodynamics of Missiles with Noncircular Bodies by : Frankie Gale Moore
Download or read book An Improved Semiempirical Method for Calculating Aerodynamics of Missiles with Noncircular Bodies written by Frankie Gale Moore and published by . This book was released on 1997 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Investigation of the Zero-lift Drag of Two Ram-jet Missile Configurations at Mach Numbers from 1.0 to 1.89 by : Clarence A. Brown
Download or read book Flight Investigation of the Zero-lift Drag of Two Ram-jet Missile Configurations at Mach Numbers from 1.0 to 1.89 written by Clarence A. Brown and published by . This book was released on 1953 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Body Alone Aerodynamics of Guided and Unguide Projectiles at Subsonic, Transonic and Supersonic Mach Numbers by : Frankie Gale Moore
Download or read book Body Alone Aerodynamics of Guided and Unguide Projectiles at Subsonic, Transonic and Supersonic Mach Numbers written by Frankie Gale Moore and published by . This book was released on 1972 with total page 146 pages. Available in PDF, EPUB and Kindle. Book excerpt: Several theoretical and empirical methods are comgined into a single computer program to predict lift, drag, and center of pressure on bodies of revolution at subsonic, transonic, and supersonic Mach numbers. The body geometries can be quite general in that pointed, spherically blunt, or truncated noses are allowed as well as discontinuities in nose shape. Particular emphasis is placed on methods which yield accuracies of ninety percent or better for most configurations but yet are computationally fast. theoretical and experimental results are presented for several projectiles and a computer program listing is included an an appendix.
Book Synopsis Aerodynamic Characteristics in Pitch of Several Triple-body Missile Configurations at Mach Numbers 0.6 to 1.4 by : Earl D. Knechtel
Download or read book Aerodynamic Characteristics in Pitch of Several Triple-body Missile Configurations at Mach Numbers 0.6 to 1.4 written by Earl D. Knechtel and published by . This book was released on 1956 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the longitudinal aerodynamic characteristics at transonic speeds of missile configurations having three blunted cone-cylinder bodies. Modifications of the basic model were tested to indicate the effects of (a) relative lengths of coplanar bodies, (b) seals between the cylindrical portions of the bodies, (c) horizontal connecting surfaces near the rear of the bodies, and (d) triangular rather than coplanar body grouping. Lift, drag, and pitching-moment data were obtained at angles of attack from -4 to 12 degrees and Mach numbers from 0.6 to 1.4 for a constant Reynolds number of 5,500,000, based on average body length.
Book Synopsis Investigation of the Lift, Center of Pressure, and Drag of a Projectile at Mach Number of 8.6 and a Reynolds Number of 17 Million by : Thomas N. Canning
Download or read book Investigation of the Lift, Center of Pressure, and Drag of a Projectile at Mach Number of 8.6 and a Reynolds Number of 17 Million written by Thomas N. Canning and published by . This book was released on 1954 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamics of Missiles Wih Offset Fin Configurations by : Gregg L. Abate
Download or read book Aerodynamics of Missiles Wih Offset Fin Configurations written by Gregg L. Abate and published by . This book was released on 1989 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamics of Tactical Weapons to Mach Number 8 and Angle of Attack 180° by : Leroy Devan
Download or read book Aerodynamics of Tactical Weapons to Mach Number 8 and Angle of Attack 180° written by Leroy Devan and published by . This book was released on 1980 with total page 192 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 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 Longitudinal Stability and Control Characteristics at Mach Numbers of 2.01, 4.65, and 6.8 of Two Hypersonic Missile Configurations, One Having Low-aspect-ratio Cruciform Wings with Trailing-edge Flaps and One Having a Flared Afterbody and All-movable Cont by :
Download or read book Longitudinal Stability and Control Characteristics at Mach Numbers of 2.01, 4.65, and 6.8 of Two Hypersonic Missile Configurations, One Having Low-aspect-ratio Cruciform Wings with Trailing-edge Flaps and One Having a Flared Afterbody and All-movable Cont written by and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 An Improved Semiempirical Method for Calculating Aerodynamics of Missiles with Noncircular Bodies by : Frank G. Moore
Download or read book An Improved Semiempirical Method for Calculating Aerodynamics of Missiles with Noncircular Bodies written by Frank G. Moore and published by . This book was released on 1997-09-01 with total page 139 pages. Available in PDF, EPUB and Kindle. Book excerpt: An improved method has been developed to compute aerodynamics of noncircular cross section shapes. The improved method is based on extending current state of the art methods for computing aerodynamics of noncircular wing- body shapes based on circular wing-body methods. Specific additions to the state of the art methods presently in use include extensions to a broader class of cross section bodies and to a higher angle of attack (AOA); extensions to allow improved accuracy at low cross flow Mach number and to allow body cross section shape to impact the critical cross flow Reynolds number; and a method to treat wing-body interference factor corrections as a function of body geometry, Mach number, and AOA. The new methods were applied to a broad class of noncircular body alone and wing body configurations for which wind tunnel data were available. In general, results for normal force, axial force and center of pressure were quite good over the Mach number and AOA range where data was available. This included Mach numbers as low as 0.3 and as high as 14 and AOAs to 60 degrees.
Book Synopsis Longitudinal Stability and Control Characteristics at a Mach Number of 2.01 of Several Simulated Air-launched Ballistic Missiles Having Various Types of Control Surfaces by : Ross B. Robinson
Download or read book Longitudinal Stability and Control Characteristics at a Mach Number of 2.01 of Several Simulated Air-launched Ballistic Missiles Having Various Types of Control Surfaces written by Ross B. Robinson and published by . This book was released on 1961 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Preliminary Design Aerodynamic Prediction Methodology for Missiles with Nose Bluntness by : Charles W. Ingram
Download or read book Preliminary Design Aerodynamic Prediction Methodology for Missiles with Nose Bluntness written by Charles W. Ingram and published by . This book was released on 1978 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt: A semi-empirical methodology is presented for predicting the axial and normal force coefficients and the center of pressure to include nose bluntness effects for missiles. This methodology includes the transonic and supersonic Mach number regime with angles of attack from 0 to 180 degrees. This methodology correlates well with wind tunnel test data. (Author).
Book Synopsis Aerodynamic Characteristics in Pitch of a Series of Cruciform-wing Missiles with Canard Controls at a Mach Number of 2.01 by : M. Leroy Spearman
Download or read book Aerodynamic Characteristics in Pitch of a Series of Cruciform-wing Missiles with Canard Controls at a Mach Number of 2.01 written by M. Leroy Spearman and published by . This book was released on 1961 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
