Static Aerodynamic Characteristics At Mach Numbers From 250 To 463 Of A Staged Airplane Model Designed For Cruise Above Mach 5
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Static Stability and Drag Characteristics of a Hypersonic Aircraft Design at Mach Numbers 1.5 to 5.6
Author | : J. T. Best (Jr.) |
Publisher | : |
Total Pages | : 122 |
Release | : 1975 |
Genre | : Drag (Aerodynamics) |
ISBN | : |
Investigation of the Static Longitudinal Aerodynamic Characteristics of a 1/10-scale Model of the Blue Scout Jr. at Mach Numbers from 0.40 to 1.03
Author | : Thomas C. Kelly |
Publisher | : |
Total Pages | : 80 |
Release | : 1962 |
Genre | : Launch vehicles (Astronautics) |
ISBN | : |
Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.20 of a Variable-wing-sweep STOL Configuration
Author | : Gerald V. Foster |
Publisher | : |
Total Pages | : 32 |
Release | : 1960 |
Genre | : Aerodynamics |
ISBN | : |
Stability and Control Characteristics at Mach Numbers of 2.50, 3.00, and 3.71 of a Variable- Wing-sweep Configuration with Outboard Wing Panels Swept Back 75°
Author | : Gerald V. Foster |
Publisher | : |
Total Pages | : 38 |
Release | : 1960 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Flight Investigation at High Mach Numbers of Several Methods of Measuring Static Pressure on an Airplane Wing
Author | : John A. Zalovcik |
Publisher | : |
Total Pages | : 26 |
Release | : 1944 |
Genre | : Aerodynamic load |
ISBN | : |
Summary: A flight investigation was made to compare static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The measurements were made on the upper surface of the wing of the P-47D airplane over a range of flight conditions in which local Mach numbers from 0.34 to 1.41 were obtained at the measurement stations. For some of the tests, a total-pressure tube was mounted on the wing surface to determine its characteristics in supersonic flow. The results indicated that static-pressure measurements obtained with suitably designed and installed flush orifices, static-pressure tubes, and static-pressure belt will be in reasonable agreement for both subsonic and supersonic flow. The pressures in supersonic flow measured by the total-pressure tube mounted on the wing surface were found to be in close agreement with values predicted by theory.
The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3
Author | : Howard F. Savage |
Publisher | : |
Total Pages | : 662 |
Release | : 1957 |
Genre | : Aerodynamics |
ISBN | : |
An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
Longitudinal Aerodynamic Characteristics of Several High-drag Bodies at Mach Numbers from 1.50 to 4.63
Author | : James F. Campbell |
Publisher | : |
Total Pages | : 44 |
Release | : 1967 |
Genre | : Aerodynamics |
ISBN | : |