Download or read book The Effects of Wing Plan Form on the Static Longitudinal Aerodynamic Characteristics of a Flat top Hypersonic Aircraft at Mach Numbers from 0 6 to 1 4 written by Stuart L. Treon and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Effects of Wing Plan Form on the Static Longitudinal Aerodynamic Characteristics of a Flat top Hypersonic Aircraft at Mach Numbers from 0 6 to 1 4 written by Stuart L. Treon and published by . This book was released on 1960 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Longitudinal Aerodynamic Characteristics of Several Hypersonic Aircraft Configurations at a Mach Number of 6 26 written by John R. Krouse and published by . This book was released on 1966 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel tests were conducted at a Mach number of 6.26 to determine the longitudinal aerodynamic characteristics of several conceptual hypersonic aircraft configurations, consisting of various half-cone-cylinder bodies and double-delta wings. Effects of body volume, vehicle orientation, wing planform, and wing-tip dihedral were determined. In general, the lift-to-drag ratios of all high-wing configurations varied slightly over an angle-of-attack range of 0 degrees to 12 degrees reaching maximum values of roughly 3.2 near 6 degrees. On the other hand, the lift-to-drag ratios of all low-wing configurations increased continuously with increasing angle of attack, eventually reaching maximum values of roughly 3.6 near 10 degrees. In all cases, fuselage base drag accounted for less than 10 percent of the total drag. For the arbitrarily chosen center-of-gravity location, all low-wing configurations were stable but unbalanced; whereas several high-wing configurations were both stable and balanced. (Author).

Download or read book Aerodynamic Characteristics at Mach 6 of a Wing body Concept for a Hypersonic Research Airplane written by James L. Dillon and published by . This book was released on 1978 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The static aerodynamic characteristics of a 1/30 scale model of a wing-body concept for a high speed research airplane were investigated in the Langley 20 inch Mach six tunnel. The investigation consisted of configuration buildup from the basic body by adding a wing, center vertical tail, three-module scramjet, and six-module scramjet engine. The test Mach number was six at a Reynolds number, based on model fuselage length, of about 13,700,000. The test angle-of-attack range was 4 to 20 D at constant angles of sideslip of 0, 2, and 4 deg. The elevons were deflected from 10 to -15 D for pitch control. Roll and yaw control were investigated. Experimental aerodynamic characteristics are compared with analytical elements.

Download or read book Static Stability and Drag Characteristics of a Hypersonic Aircraft Design at Mach Numbers 1 5 to 5 6 written by J. T. Best (Jr.) and published by . This book was released on 1975 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Longitudinal Aerodynamic Characteristics of Several Hypersonic Aircraft Configurations at a Mach Number of 9 45 written by John R. Krouse and published by . This book was released on 1966 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel tests were conducted at a Mach number of 9.45 to determine the longitudinal aerodynamic characteristics of several conceptual hypersonic aircraft configurations, consisting of various half-cone-cylinder bodies and double-delta wings. Effects of body volume, vehicle orientation, wing planform, and wing-tip dihedral were determined. In general, the lift-to-drag ratios of all high-wing configurations varied slightly over an angle-of-attack range of 0 degrees to 12 degrees, reaching a maximum value of 2.7 around 6 degrees. On the other hand, the lift-to-drag ratios of all low-wing configurations increased continuously with increasing angle of attack, eventually reaching maximum values of roughly 3.0 near 12 degrees. In all cases, fuselage base drag accounted for less than 4 percent of the total drag. For the arbitrarily chosen center-of-gravity location, all low-wing configurations were unstable, unbalanced, or both; whereas several high-wing configurations were both stable and balanced. (Author).

Download or read book Aerodynamic Characteristics at Mach 6 of a Hypersonic Research Airplane Concept Having a 70 swept Delta Wing written by Louis E. Clark and published by . This book was released on 1977 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Static Longitudinal Aerodynamic Characteristics at a Mach Number of 10 03 of Low aspect ratio Wing body Configurations Suitable for Reentry written by and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of a Hypersonic Research Airplane Concept Having a 70 Deg Swept Double delta Wing at Mach Numbers from 0 80 to 1 20 with Summary of Data from 0 20 to 6 0 written by and published by . This book was released on 1979 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Mach Numbers of 1 5 1 8 and 2 0 of a Blended Wing body Configuration with and Without Integral Canards written by A. Warner Robins and published by . This book was released on 1979 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of Wing body and Lifting body Configurations of Hypersonic Cruise Aircraft at Mach 2 30 to 4 63 written by Lloyd S. Jernell and published by . This book was released on 1971 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Some Effects of Aircraft Configuration on Static Longitudinal and Directional Stability Characteristics at Supersonic Mach Numbers Below 3 written by M. Leroy Spearman and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Longitudinal and Directional Aerodynamic Characteristics of Several Hypersonic Aircraft Configurations written by John R. Krouse and published by . This book was released on 1967 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were conducted at a Mach number of 9.45 to determine the aerodynamic characteristics of several conceptual hypersonic aircraft configurations consisting of various half-cone-cylinder bodies and double-delta wings. Effects of body volume, wing planform, and wing-tip deflection on static directional stability were determined. In addition, the effects of wing thickness on the aerodynamic efficiency were obtained. Decreasing body volume, extending the trailing edges, and deflecting the wing tips (toward or away from the fuselage) were all directionally stabilizing. Decreasing wing thickness significantly increased maximum untrimmed lift-to-drag ratios.

Download or read book Effects of Body Shape on the Aerodynamic Characteristics of an All body Hypersonic Aircraft Configuration at Mach Numbers from 0 65 to 10 6 written by Walter P. Nelms and published by . This book was released on 1972 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of an All body Hypersonic Aircraft Configuration at Mach Numbers from 0 65 to 10 6 written by Walter P. Nelms and published by . This book was released on 1971 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft are presented for Mach numbers from 0.65 to 10.6. The configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section. Detailed effects of varying angle of attack (-2 to 15 deg), angle of sideslip (-2 to 8 deg), Mach number, and configuration buildup were considered. In addition, the effectiveness of horizontal tail, vertical tail, and canard stabilizing and control surfaces was investigated. The results indicate that all configurations were longitudinally stable near maximum lift drag ratio. The configurations with vertical tails were directionally stable at all angles of attack. Trim penalties were small at hypersonic speeds for a center of gravity location representative of the airplane, but because of the large rearward travel of the aerodynamic center, trim penalties were severe at transonic Mach numbers.

Download or read book Effects of Wing Elevation Incidence and Camber on the Aerodynamic Characteristics of a Representative Hypersonic Cruise Configuration at Mach Numbers from 0 65 to 10 70 written by Walter P. Nelms and published by . This book was released on 1970 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Flight Stability and Automatic Control written by Robert C. Nelson and published by WCB/McGraw-Hill. This book was released on 1998 with total page 441 pages. Available in PDF, EPUB and Kindle. Book excerpt: The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.