Download or read book The Calculation of Aerodynamic Characteristics of Wing body Combinations at Subsonic Flight Speeds written by W. Loeve and published by . This book was released on 1976 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by Ross B. Robinson and published by . This book was released on 1952 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by Lowell E. Hasel and published by . This book was released on 1952 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Properties of Cruciform wing and Body Combinations at Subsonic Transonic and Supersonic Speeds written by John R. Spreiter and published by . This book was released on 1949 with total page 646 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic forces and moments exerted on pitched and yawed wing-body combinations consisting of a slender body of revolution and a cruciform arrangement of thin wings have been investigated by two theoretical methods. One method, an extension of the slender wing-body theory of NACA TN No. 1662, makes possible the determination of simple closed expressions for the load distribution, of simple closed expressions for the load distribution, the forces, and the moments for slender cruciform-wing and body combinations in which the wings may be dissimilar plan form. The second method treats cruciform-wing and body combinations consisting of a body of revolution and identical wings of arbitrary aspect ratio and plan form. The results are valid at subsonic, transonic, and supersonic speeds.

Download or read book Aerodynamic Properties of Slender Wing body Combinations at Subsonic Transonic and Supersonic Speeds written by John R. Spreiter and published by . This book was released on 1948 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: It is further shown that the aerodynamic characteristics of a moderate-aspect-ratio pointed wing at sonic speed may be predictied in a manner mathematically equivalent to that used in the study of a low-aspect-ratio wing.

Download or read book A Computer Program for the Prediction of Aerodynamic Characteristics of Wing body tail Combinations at Subsonic and Supersonic Speeds written by S. Anders and published by . This book was released on 1972 with total page 119 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Integrated Approach to the Analysis and Design of Wings and Wing body Combinations in Supersonic Flow written by Ralph L. Carmichael and published by . This book was released on 1966 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by M. Leroy Spearman and published by . This book was released on 1952 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Method for Calculating the Aerodynamic Loading on Wing body Combinations at Small Angles of Attack in Supersonic Flow written by Charlie M. Jackson and published by . This book was released on 1971 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a theoretical method for estimating the aerodynamic loading on a wing-body configuration. In order to provide a basis for evaluation of the method, experimental measurements of surface pressures, forces, and moments were made on a series of basic wing-body configurations over a Mach number range from 2.5 to 4.5. Comparison of the theoretical estimates with these experimental data generally indicated good agreement for the entire range of configurations and test conditions.

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by Cornelius Driver and published by . This book was released on 1952 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 Effects of Sweep Angle and Thickness Ratio on the Aerodynamic Characteristics in Pitch at 0 2 written by Ross B. Robinson and published by . This book was released on 1952 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by Clyde V. Hamilton and published by . This book was released on 1952 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Estimation at Subsonic Speeds of the Longitudinal and Lateral Aerodynamic Characteristics of Wing body Combinations at Angle Up to 90 Degrees written by K. D. Thomson and published by . This book was released on 1976 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of Several Cranked Leading edge Wing body Combinations at Mach Numbers from 0 4 to 2 94 written by Edward J. Hopkins and published by . This book was released on 1967 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Theoretical Investigation of the Aerodynamics of Wing tail Combinations Performing Time dependent Motions at Supersonic Speeds written by John C. Martin and published by . This book was released on 1954 with total page 720 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical investigation is presented of the contribution of horizontal tails to the lift and pitching moment due to angle of attack, a constant rate of pitch, and a constant vertical acceleration. Numerical values of the aerodynamic coefficients associated with these motions are presented for a number of two-dimensional wing-tail combinations, a triangular wing-tail combination, and a number of rectangular-wing - triangular-tail combinations.

Download or read book Aircraft Configurations Developing High Lift drag Ratios at High Supersonic Speeds written by A. J. Eggers (Jr.) and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The problem of designing an aircraft which will develop high lift-drag ratios in flight at high supersonic speeds is attacked using the elementary principle that the components of the aircraft should be individually and collectively arranged to impart the maximum downward and the minimum forward momentum to the surrounding air. This principle in conjunction with other practical considerations of hypersonic flight leads to the study of configurations for which the body is situated entirely below the wing; that is, flat-top wing-body combinations. Theory indicates that sensibly complete aircraft of this type can be designed to develop lift-drag ratios well in excess of 6.

Download or read book An Improved Method for the Aerodynamic Analysis of Wing body tail Configurations in Subsonic and Supersonic Flow Computer program description written by F. A. Woodward and published by . This book was released on 1973 with total page 324 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new method has been developed for calculating the pressure distribution and aerodynamic characteristics of wing-body-tail combinations in subsonic and supersonic potential flow. A computer program has been developed to perform the numerical calculations. The configuration surface is subdivided into a large number of panels, each of which contains an aerodynamic singularity distribution. A constant source distribution is used on the body panels, and a vortex distribution having a linear variation in the streamwise direction is used on the wing and tail panels. The normal components of velocity induced at specified control points by each singularity distribution are calculated and make up the coefficients of a system of linear equations relating the strengths of the singularities to the magnitude of the normal velocities.