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Investigation Of The Lift Center Of Pressure And Drag Of A Projectile At Mach Number Of 86 And A Reynolds Number Of 17 Million
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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 Index to NASA Technical Publications by : United States. National Aeronautics and Space Administration
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation at a Mach Number of 3.11 of the Lift, Drag, and Pitching-moment Characteristics of Five Blunt Lifting Bodies by : William Letko
Download or read book Experimental Investigation at a Mach Number of 3.11 of the Lift, Drag, and Pitching-moment Characteristics of Five Blunt Lifting Bodies written by William Letko and published by . This book was released on 1960 with total page 22 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 Effect of Reynolds Number on the Force and Pressure Distribution Characteristics of a Two-Dimensional Lifting Circular Cylinder by : Vernard E. Lockwood
Download or read book Effect of Reynolds Number on the Force and Pressure Distribution Characteristics of a Two-Dimensional Lifting Circular Cylinder written by Vernard E. Lockwood and published by . This book was released on 1960 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Reynolds Number Effect on Drag of the Angled Arrow Projectile by : I. M. Nestingen
Download or read book Reynolds Number Effect on Drag of the Angled Arrow Projectile written by I. M. Nestingen and published by . This book was released on 1951 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of a series of shots fired in the NOL pressurized ballistics firing range to determine the effect of Reynolds number on drag of the Angled Arrow Projectile at Mach numbers of 1.86 and 2.87. Drag values were determined for a Reynolds number variation of nine million. The results obtained at M = 1.86 indicate an increase in drag coefficient of approximately 4.55 per cent for a change in Reynolds number from 2,000,000 to 11,000,000. At M - 2.87 an increase in drag coefficient of approximately 20 percent was obtained for a similar variation in Reynolds number. The drag values are in fair agreement with wind-tunnel tests and with the estimated free-flight values of the full-scale missile at high altitude.
Book Synopsis Design for Control of Projectile Flight Characteristics by :
Download or read book Design for Control of Projectile Flight Characteristics written by and published by . This book was released on 1966 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Elevon Deflection and of Model Components on Aerodynamic Characteristics of a Manned Lifting Entry Vehicle at Mach Numbers of 0.20 to 1.20 by :
Download or read book Effect of Elevon Deflection and of Model Components on Aerodynamic Characteristics of a Manned Lifting Entry Vehicle at Mach Numbers of 0.20 to 1.20 written by and published by . This book was released on 1966 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis New Methods for Predicting Nonlinear Lift, Center of Pressure, and Pitching Moment on Middile Configurations by : Frankie Gale Moore
Download or read book New Methods for Predicting Nonlinear Lift, Center of Pressure, and Pitching Moment on Middile Configurations written by Frankie Gale Moore and published by . This book was released on 1992 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new semiempirical method has been developed to predict normal force, pitching moment, and center of pressure on missile configurations up to angles of attack of 30° The method is based on linear theory and slender body techniques at low angle of attack and uses wind tunnel data to derive nonlinear angle-of-attack corrections as angle of attack increaces. The new improved theories include body alone, wing alone, and body-wing and wing-body interference. While the new theory is databased, simple analytical formulas are derived that allow general use of the techniques. Comparison with the linearized approaches used in the former NSWCDD aeroprediction code shows singificant reductions in errors of aerodynamics above 5° to 10° angle of attack. Limited comparisons to other state-of-the-art engineering codes show the new theory to be as good as or better than anything known to be available for computing planar aerodynamics up to 30° angle of attack.
Book Synopsis Heat-transfer Tests of 20-millimeter Projectiles at a Mach Number of 5 with an Analysis by Unsteady Scaling Laws to Predict Component Temperature Rises After Firing for Various Free-flight Conditions by : Robert L. Trimpi
Download or read book Heat-transfer Tests of 20-millimeter Projectiles at a Mach Number of 5 with an Analysis by Unsteady Scaling Laws to Predict Component Temperature Rises After Firing for Various Free-flight Conditions written by Robert L. Trimpi and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental and Computational Results of a Maneuverable Power-Law Elliptic Cross-Section Projectile at Supersonic Speeds by : John J. Bertin
Download or read book Experimental and Computational Results of a Maneuverable Power-Law Elliptic Cross-Section Projectile at Supersonic Speeds written by John J. Bertin and published by . This book was released on 2001-10-01 with total page 77 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents the results of an experimental and computational investigation of a power-law elliptic cross-section projectile for increased maneuverability. Surface-pressure measurements and force-and-moment measurements have been conducted in the Tri-Sonic Wind-Tunnel (TWT) at the Aerodynamic Research Center (ARC) at the U.S. Air Force Academy. Flow visualization data were also obtained in the form of Schlieren photographs and surface oil-flow patterns during these test programs. Data were obtained at a Mach number of 4.2% over a range of Reynolds numbers (based on the free-stream conditions and the model length) of 12.47 million to 19.96 million over an angle-of-attack range from -11 to +11 degrees. The data from these wind-tunnel tests were compared with computations generated using the Cobalt code, which was run on the Beowulf cluster at the High-Performance Computing Facility (HPCF) at the ARC. It should be noted that the experimental and the computational parts of this investigation were conducted concurrently in a double-blind fashion. That is, the results from the experimental effort were not used to influence the way in which the results from the CFD effort were produced and vice versa. Free flight investigations were carried out at the U.S. Air Force Research Laboratory Munitions Directorate Aeroballistic Research Facility and were conducted at Mach numbers ranging from 3.0 to 5.0. The free flight experimental data consisted of nine free-flight projectiles launched within an instrumented facility. Additional computational work was again carried out via the Cobalt code at the flight conditions of the experimental facility. The results indicate good agreement between the experimental and computational data determined in this effort, as well as, with engineering level predictions. The free-flight data was limited to small angles of attack therefore high fidelity determination of the aerodynamic stability coefficients and derivatives was not possib7
Book Synopsis Lift and Drag Characteristics of the HL-10 Lifting Body During Subsonic Gliding Flight by : Jon S. Pyle
Download or read book Lift and Drag Characteristics of the HL-10 Lifting Body During Subsonic Gliding Flight written by Jon S. Pyle and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of a Hemispherical Base on the Aerodynamic Characteristics of Shell by : Ralph E. Deitrick
Download or read book Effect of a Hemispherical Base on the Aerodynamic Characteristics of Shell written by Ralph E. Deitrick and published by . This book was released on 1955 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unsteady loads due to propulsive lift configurations, part a by : Jeffrey B. Morton
Download or read book Unsteady loads due to propulsive lift configurations, part a written by Jeffrey B. Morton and published by . This book was released on 1978 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Lift, Drag, and Pitching Moment of a 60 Deg Delta-Wing-Body Combination (AGARD Calibration Model B) in the Langley 9-Inch Supersonic Tunnel by :
Download or read book Investigation of Lift, Drag, and Pitching Moment of a 60 Deg Delta-Wing-Body Combination (AGARD Calibration Model B) in the Langley 9-Inch Supersonic Tunnel written by and published by . This book was released on 1954 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: The lift, drag, and pitching-moment characteristics of the AGARD Calibration Model B as determined in the Langley 9-inch supersonic tunnel are presented at Mach numbers of 1.62, 1.94, and 2.41 and at a Reynolds number, based on body length, of approximately 3.0 x 10(exp 6). The zero-lift drag data compared favorably with available data and were in the proper sequence for the effects of Reynolds number.
Book Synopsis Static Stability and Control Characteristics of a Right Triangular Pyramid Lifting Reentry Configuration at a Mach Number of 10.03 by :
Download or read book Static Stability and Control Characteristics of a Right Triangular Pyramid Lifting Reentry Configuration at a Mach Number of 10.03 written by and published by . This book was released on 1964 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1991 with total page 718 pages. Available in PDF, EPUB and Kindle. Book excerpt:
