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Free Flight Measurements Of The Rolling Effectiveness And Drag Of Trailing Edge Spoilers On A Tapered Sweptback Wing At Mach Numbers Between 0 6 And 1 4 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 Free Flight Measurements Of The Rolling Effectiveness And Drag Of Trailing Edge Spoilers On A Tapered Sweptback Wing At Mach Numbers Between 0 6 And 1 4 book. This book definitely worth reading, it is an incredibly well-written.
Author : Eugene D. Schult,E. M. Fields
Publisher : Unknown
Page : 18 pages
File Size : 53,7 Mb
Release : 1954
Category : Airplanes
ISBN : UOM:39015095100775
Author : Roland D. English
Publisher : Unknown
Page : 20 pages
File Size : 41,5 Mb
Release : 1954
Category : Ailerons
ISBN : UOM:39015095100809
Author : Anonim
Publisher : Unknown
Page : 388 pages
File Size : 40,8 Mb
Release : 1957
Category : Aeronautics
ISBN : UVA:X004173287
Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 388 pages
File Size : 42,5 Mb
Release : 1959
Category : Aeronautics
ISBN : UCBK:C029901327
Author : John D. Morrow
Publisher : Unknown
Page : 30 pages
File Size : 48,8 Mb
Release : 1950
Category : Aerodynamic load
ISBN : UOM:39015086464651
Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models having rectangular 6-percent-thick wings are presented for a Mach number range of 0.6 to 1.7. Wings of aspect ratio 2.7 having diamond, circular-arc, and blunt-trailing edge airfoil sections were tested. Pressures were measured on the base of the blunt-trailing-edge airfoil which had a rectangular section with a 40-percent-chord beveled leading edge. Although the blunt-trailing-edge airfoil had high drag throughout the Mach number range investigated, because of high base suction pressures, it is believed that the data presented can be used in the design of more nearly optimum blunt-base airfoils. Of the airfoils tested the circular-arc section had lowest drag at high-subsonic speeds, and the diamond section had lowest drag at supersonic speeds.
Author : Kenneth Margolis
Publisher : Unknown
Page : 724 pages
File Size : 44,7 Mb
Release : 1948
Category : Aerodynamics, Supersonic
ISBN : STANFORD:36105024795655
Wave drag equations are derived for rhombic-profile tapered wings with maximum-thickness line swept less than the Mach line. Variations in drag with taper ratio, aspect ratio, sweepback, and Mach number are determined. Calculations are presented for representative plan forms and for a family of wings having equal root bending stress.
Author : Roland D. English
Publisher : Unknown
Page : 22 pages
File Size : 50,5 Mb
Release : 1954
Category : Ailerons
ISBN : UOM:39015086465633
The Langley Pilotless Aircraft Research Division has made an investigation to determine some effects of external wing tip tanks on the rolling effectiveness and drag of plain and half-delta tip ailerons on a 4-percent-thick, tapered, unswept wing. The investigation was made by means of a rocket-propelled models in free flight over a range of Mach numbers from 0.6 to 1.5.
Author : John D. Morrow,Ellis Katz
Publisher : Unknown
Page : 19 pages
File Size : 43,9 Mb
Release : 1955
Category : Electronic
ISBN : OCLC:249833929
Author : Albert D. Hemenover,Donald J. Graham
Publisher : Unknown
Page : 756 pages
File Size : 46,7 Mb
Release : 1954
Category : Aerofoils
ISBN : STANFORD:36105024831807
The effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap are appraised from wind-tunnel tests at Mach numbers from 0.3 to 0.9 and Reynolds numbers varying correspondingly from 1 to 2 million. The airfoil trailing-edge angle was varied from approximately 18 to 6 degrees, and the trailing-edge thickness from zero to the thickness at the flap hinge line.
Author : Anonim
Publisher : Unknown
Page : 34 pages
File Size : 52,7 Mb
Release : 1949
Category : Aeronautics
ISBN : MINN:31951D008217381
Author : Douglas R. Lord
Publisher : Unknown
Page : 52 pages
File Size : 44,8 Mb
Release : 1957
Category : Aerodynamics
ISBN : UOM:39015086466151
An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of a spoiler-slot-deflector control on a 45 degree sweptback wing having an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. The model was equipped with a 15-percent-chord spoiler-slot-deflector extending from 13 o 78 percent of the wing semispan. The spoiler and deflector were hinged along the 60- and 75-percent-chord lines, respectively. Tests were made at a Reynolds number of 3,000,000 (based on the mean aerodynamic chord of the wing) and covered ranges of angles of attack from -3 to 15 degrees, spoiler projections from 0 to 8.0 percent chord, and deflector projections from 0 to 7.6 percent chord.
Author : Lawrence Duncan Guy,Hoyt V. Brown
Publisher : Unknown
Page : 42 pages
File Size : 43,8 Mb
Release : 1955
Category : Airplanes
ISBN : UOM:39015086506998
Author : Alexander D. Hammond
Publisher : Unknown
Page : 26 pages
File Size : 54,7 Mb
Release : 1954
Category : Airplanes
ISBN : UOM:39015095100759
Author : Emma Jean Landrum,K. R. Czarnecki
Publisher : Unknown
Page : 70 pages
File Size : 52,9 Mb
Release : 1960
Category : Aerofoils
ISBN : UIUC:30112106589283
Author : Lawrence D. Guy
Publisher : Unknown
Page : 52 pages
File Size : 46,6 Mb
Release : 1954
Category : Aerodynamics, Supersonic
ISBN : UOM:39015095100817
A wind-tunnel investigation has been made of two unswept, partial-span, flap-type controls (differing only in hinge-line location) mounted on a 60 degree delta wing. One control was unbalanced and the other has a 100-percent overhang balance. Control hinge moments as well as aerodynamic characteristics of the complete wing-body combination were obtained for control deflections from 0 to 40 degrees over an angle-of-attack range of plus or minus 12 degrees at Mach numbers from 0.75 to 1.96. Reynolds numbers varied between 2,200,000 and 2,200,000. Expressions derived from linear theory for the hinge-moment coefficient due to angle of attack for unswept partial-span controls (which extend neither to the wing tip nor to the wing center line) on triangular wings having subsonic leading edges are given in an appendix.
