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Investigation Of The Aerodynamic Characteristics Of The Naca Rm 10 Missile With Fins At A Mach Number Of 162 In The Langley 9 Inch Supersonic Tunnel
Download Investigation Of The Aerodynamic Characteristics Of The Naca Rm 10 Missile With Fins At A Mach Number Of 162 In The Langley 9 Inch Supersonic Tunnel full books in PDF, epub, and Kindle. Read online Investigation Of The Aerodynamic Characteristics Of The Naca Rm 10 Missile With Fins At A Mach Number Of 162 In The Langley 9 Inch Supersonic Tunnel ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (with Fins) at a Mach Number of 1.62 in the Langley 9-inch Supersonic Tunnel by : Donald E. Coletti
Download or read book Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (with Fins) at a Mach Number of 1.62 in the Langley 9-inch Supersonic Tunnel written by Donald E. Coletti and published by . This book was released on 1952 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 by : Roger W. Luidens
Download or read book Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 written by Roger W. Luidens and published by . This book was released on 1950 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 by : Roger W. Luidens
Download or read book Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 written by Roger W. Luidens and published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Preliminary Investigation of the Drag Characteristics of the NACA RM-10 Missile at Mach Numbers of 1.40 and 1.59 in the Langley 4- by 4-foot Supersonic Tunnel by : Lowell E. Hasel
Download or read book Preliminary Investigation of the Drag Characteristics of the NACA RM-10 Missile at Mach Numbers of 1.40 and 1.59 in the Langley 4- by 4-foot Supersonic Tunnel written by Lowell E. Hasel and published by . This book was released on 1952 with total page 49 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of the NACA RM-10 Research Missile in the Ames 1- by 3-foot Supersonic Wind Tunnel No. 2 - Pressure and Force Measurements at Mach Numbers of 1.52 and 1.98 by : Edward W. Perkins
Download or read book Aerodynamic Characteristics of the NACA RM-10 Research Missile in the Ames 1- by 3-foot Supersonic Wind Tunnel No. 2 - Pressure and Force Measurements at Mach Numbers of 1.52 and 1.98 written by Edward W. Perkins and published by . This book was released on 1951 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 by : Fred T. Esenwein
Download or read book Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 written by Fred T. Esenwein and published by . This book was released on 1950 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NACA Research Memorandum written by and published by . This book was released on 19?? with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 by : Roger W. Luidens
Download or read book Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 written by Roger W. Luidens and published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the Characteristics of the NACA RM-10 (with and Without Fins) in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.9 by : William D. McCauley
Download or read book An Investigation of the Characteristics of the NACA RM-10 (with and Without Fins) in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.9 written by William D. McCauley and published by . This book was released on 1954 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of the NACA RM-10 Research Missile in the Ames 1- by 3-foot Supersonic Wind Tunnel by : Edward W. Perkins
Download or read book Aerodynamic Characteristics of the NACA RM-10 Research Missile in the Ames 1- by 3-foot Supersonic Wind Tunnel written by Edward W. Perkins and published by . This book was released on 1952 with total page 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 Aerodynamic Investigation at Mach Number 1.92 of a Rectangular Wing and Tail and Body Configuration and Its Components by : Macon C. Ellis
Download or read book Aerodynamic Investigation at Mach Number 1.92 of a Rectangular Wing and Tail and Body Configuration and Its Components written by Macon C. Ellis and published by . This book was released on 1950 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at Mach number 1.92 in the Langley 9-inch supersonic tunnel of a variable body-wing-tail configuration has been made in order to determine and to isolate the aerodynamic effects on each other of the components of the configuration.
Book Synopsis Experimental Study at Low Supersonic Speeds of a Missile Concept Having Opposing Wraparound Tails by : Jerry M. Allen
Download or read book Experimental Study at Low Supersonic Speeds of a Missile Concept Having Opposing Wraparound Tails written by Jerry M. Allen and published by . This book was released on 1994 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: A wind-tunnel investigation has been performed at low supersonic speeds (at Mach numbers of 1.60, 1.90, and 2.16) to evaluate the aerodynamic characteristics of a missile concept capable of being tube launched and controlled with a simple one-axis canard controller. This concept, which features and axisymmetric body with two planar canards and four wraparound tail fins arranged in opposing pairs, must be in rolling motion to be controllable in any radial plane with the planar canards. Thus, producing a constant rolling moment that is invariant with speed and attitude to provide the motion is desirable. Two tail-fin shaping designs, one shaved and one beveled, were evaluated for their efficiency in producing the needed rolling moments, and the results showed that the shaved fins were much more desirable for this task than the beveled fins.
Book Synopsis Investigation of the Aerodynamic Characteristics of a Model of a Rocket Missile with Several Arrangements of Folding Fins at Mach Numbers of 1.75, 2.15, 2.48, and 2.87 by :
Download or read book Investigation of the Aerodynamic Characteristics of a Model of a Rocket Missile with Several Arrangements of Folding Fins at Mach Numbers of 1.75, 2.15, 2.48, and 2.87 written by and published by . This book was released on 1960 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins by : James DeSpirito
Download or read book Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins written by James DeSpirito and published by . This book was released on 2004 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt: Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flow field around a canard-controlled missile in subsonic and transonic flow. Computations were performed at Mach 0.6 and 0.9, six angles of attack between 0 deg and 10 deg, and with planar and grid tail fins. The computations were validated with wind tunnel data. Flow visualizations showed that the canard downwash produced a low-pressure region on the starboard side of the missile that produced a large induced side force. The canard trailing vortices interacted with the tail fins until alpha> 8 deg, producing a pressure differential on the leeward tail fin, leading to the adverse induced roll effects. Visualizations of the flow through the grid fin structure showed choking of the flow at Mach 0.9 and Mach 1.5. The validated simulations results showed that grid fins did not improve the canard roll-control effectiveness at subsonic and transonic speeds as well as they did at the low supersonic speed.
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 1.47 to 4.62 of Static Aerodynamic Characteristics of Twelve Nose Cones Designed for Supersonic Impact by :
Download or read book Wind-tunnel Investigation at Mach Numbers from 1.47 to 4.62 of Static Aerodynamic Characteristics of Twelve Nose Cones Designed for Supersonic Impact written by and published by . This book was released on 1961 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
