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A Wind Tunnel Investigation Of The Aerodynamic Characteristics Of Bodies Of Revolution At Mach Numbers Of 2 37 2 98 And 3 90 At Angles Of Attack To 90 Deg Book in PDF, ePub and Kindle version is available to download in english. Read online anytime anywhere directly from your device. Click on the download button below to get a free pdf file of A Wind Tunnel Investigation Of The Aerodynamic Characteristics Of Bodies Of Revolution At Mach Numbers Of 2 37 2 98 And 3 90 At Angles Of Attack To 90 Deg book. This book definitely worth reading, it is an incredibly well-written.
Author : Anonim
Publisher : Unknown
Page : 106 pages
File Size : 41,8 Mb
Release : 1975
Category : Electronic
ISBN : NASA:31769000534480
Author : Anonim
Publisher : Unknown
Page : 104 pages
File Size : 45,9 Mb
Release : 1979
Category : Electronic
ISBN : NASA:31769000541303
Author : Anonim
Publisher : Unknown
Page : 344 pages
File Size : 55,9 Mb
Release : 1986
Category : Fluid dynamics
ISBN : STANFORD:36105001804769
Author : Harry W. Carlson,John P. Gapcynski
Publisher : Unknown
Page : 36 pages
File Size : 48,8 Mb
Release : 1955
Category : Aerodynamics
ISBN : UFL:31262081065954
Abstract: An experimental investigation has been performed to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and given longitudinal distribution of cross-sectional area but various cross-section shapes were tested at a Mach number of 2.01. The bodies were tested alone and in combination with a 47° sweptback wing having a 6-percent-thick hexagonal section.
Author : John W. Draper
Publisher : Unknown
Page : 82 pages
File Size : 42,6 Mb
Release : 1954
Category : Aerodynamics
ISBN : UOM:39015086496323
This report presents the results of an investigation conducted in the Langley 300 mph 7- 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.
Author : Leland Howard Jorgensen
Publisher : Unknown
Page : 88 pages
File Size : 50,9 Mb
Release : 1975
Category : Aerodynamics
ISBN : UIUC:30112106563718
An experimental investigation was conducted in the Ames 6- by 6-Foot Wind Tunnel to measure the static aerodynamic characteristics for two bodies of elliptic cross section and for their equivalent body of revolution. The equivalent body of revolution had the same length and axial distribution of cross-sectional area as the elliptic bodies. It consisted of a tangent ogive nose of fineness ratio 3 followed by a cylinder with a fineness ratio of 7. For the first body of elliptic cross section, the ratio of the semimajor axis to semiminor axis was held constant at 2 all along the body length. For the second elliptic body the nose was unchanged, but the aftersection was changed as follows: The cross-sectional axis ratio a/b was decreased from 2 to 1 over an axial distance of about 1.66 diam. Then, at this position, the a,b axis system was rotated 900, and the a/b ratio was increased back to 2 over the next 2.34 diam in length. Over the last length of three body diam, this rotated a/b ratio was held constant at 2.
Author : Thomas C. Kelly
Publisher : Unknown
Page : 82 pages
File Size : 45,6 Mb
Release : 1957
Category : Aerodynamic load
ISBN : UOM:39015086507152
Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.
Author : Anonim
Publisher : Unknown
Page : 980 pages
File Size : 51,8 Mb
Release : 1998
Category : Aeronautics
ISBN : STANFORD:36105021106690
Author : Paul G. Fournier
Publisher : Unknown
Page : 34 pages
File Size : 44,5 Mb
Release : 1953
Category : Airplanes
ISBN : UOM:39015086490300
The results presented in the present paper are part of a program conducted to investigate the effect of wing plan form on the aerodynamic characteristics in pitch, in sideslip, and during steady roll. This paper presents the aerodynamic characteristics in pitch and sideslip at high subsonic speeds of a wing-fuselage combination having a triangular wing of aspect ratio 4, a leading-edge sweep of angle of 45 degrees, and with an NACA 65A006 airfoil section parallel to the plane of symmetry.
Author : Leland Howard Jorgensen
Publisher : Unknown
Page : 100 pages
File Size : 55,5 Mb
Release : 1974
Category : Aerodynamics
ISBN : UIUC:30112106563700
Author : Walter P. Nelms,Charles L. Thomas
Publisher : Unknown
Page : 108 pages
File Size : 45,6 Mb
Release : 1971
Category : Aerodynamics, Hypersonic
ISBN : UIUC:30112106692616
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.
Author : New Brunswick. Department of Transportation
Publisher : Unknown
Page : 1272 pages
File Size : 40,7 Mb
Release : 1991
Category : Electronic
ISBN : 1550483927
General activity review of associated branches and agencies to the Department which includes corporate securities registrations, a list of tenders received, and general financial data. Branches and agencies reviewed are responsible for motor vehicle activity, highway construction, traffic engineering, telecommunications and public utilities.
Author : Kenneth P. Spreemann
Publisher : Unknown
Page : 644 pages
File Size : 47,6 Mb
Release : 1957
Category : Airplanes
ISBN : STANFORD:36105024832128
This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.
Author : Anonim
Publisher : Unknown
Page : 1290 pages
File Size : 51,8 Mb
Release : 1991-06
Category : Science
ISBN : CORNELL:31924050822125
Author : Dennis E. Fuller,Victor E. Langhans
Publisher : Unknown
Page : 38 pages
File Size : 53,8 Mb
Release : 1963
Category : Aerodynamics
ISBN : UIUC:30112106864447
