Investigation At Mach Numbers Of 020 To 350 Of A Blended Diamond Wing And Body Combination Of Sonic Design But With Low Wave Drag Increase With Increasing Mach Number
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Investigation at Mach Numbers of 0.20 to 3.50 of Blended Wing-body Combinations of Sonic Design with Diamond, Delta and Arrow Plan Forms
Author | : George H. Holdaway |
Publisher | : |
Total Pages | : 82 |
Release | : 1960 |
Genre | : Aerodynamics |
ISBN | : |
Investigation at Mach Numbers of 0.60 to 3.50 of Blended Wing-body Combinations with Cambered and Twisted Wings with Diamond, Delta and Arrow Plan Forms
Author | : George H. Holdaway |
Publisher | : |
Total Pages | : 80 |
Release | : 1961 |
Genre | : Aerodynamics |
ISBN | : |
A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios
Author | : Richard T. Whitcomb |
Publisher | : |
Total Pages | : 20 |
Release | : 1960 |
Genre | : Airplanes |
ISBN | : |
Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
Free-flight Measurements of the Zero-lift Drag of Several Wings at Mach Numbers from 1.4 to 3.8
Author | : H. Herbert Jackson |
Publisher | : |
Total Pages | : 32 |
Release | : 1960 |
Genre | : Mach number |
ISBN | : |
Investigation of the Drag of Blunt-nosed Bodies of Revolution in Free Flight at Mach Numbers from 0.6 to 2.3
Author | : Harvey A. Wallskog |
Publisher | : |
Total Pages | : 32 |
Release | : 1953 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-wedge Sections with the Maximum Thickness at 0.18 Chord
Author | : Mitchel H. Bertram |
Publisher | : |
Total Pages | : 58 |
Release | : 1954 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
A program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section has been conducted at the Langley 11-inch hypersonic tunnel. These wings had a maximum thickness of 8 percent of the chord located at the 18-percent-chord point. For the wings tested at a Mach number of 6.9, the semiapex angle was varied from 5 to 30 degrees and the wings were tested over a range of angle of attack from 0 to 28 degrees and Reynolds numbers in the range of 800,000 to 3,600,000 based on root chord. In addition, pertinent results from tests at Mach number as low as 1.62 have been utilized. The shock-expansion theory and the Newtonian impact theory have been used to analyze the effects of changes made in the various parameters investigated.