Download Full eBooks in PDF
Effects At Mach Numbers Of 1 61 And 2 01 Of Camber And Twist On The Aerodynamic Characteristics Of Three Swept Wings Having The Same Planform 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 Effects At Mach Numbers Of 1 61 And 2 01 Of Camber And Twist On The Aerodynamic Characteristics Of Three Swept Wings Having The Same Planform book. This book definitely worth reading, it is an incredibly well-written.
Author : United States. National Aeronautics and Space Administration
Publisher : Unknown
Page : 128 pages
File Size : 50,6 Mb
Release : 1960-07
Category : Electronic
ISBN : STANFORD:36105024165701
Author : Anonim
Publisher : Unknown
Page : 962 pages
File Size : 47,5 Mb
Release : 1962
Category : Aeronautics
ISBN : UOM:39015010883034
Author : Anonim
Publisher : Unknown
Page : 652 pages
File Size : 53,6 Mb
Release : 1959
Category : Aerodynamics
ISBN : COLUMBIA:1001422880
Author : Royal Aeronautical Society
Publisher : Unknown
Page : 1164 pages
File Size : 45,5 Mb
Release : 1962
Category : Aeronautics
ISBN : MINN:319510006533321
Author : Anonim
Publisher : Unknown
Page : 260 pages
File Size : 45,6 Mb
Release : 1977
Category : Aeronautics
ISBN : MINN:30000006324416
Author : Joseph Adams Shortal
Publisher : Unknown
Page : 808 pages
File Size : 45,5 Mb
Release : 1978
Category : Aeronautics
ISBN : STANFORD:36105024718376
Author : Anonim
Publisher : Unknown
Page : 44 pages
File Size : 48,8 Mb
Release : 1960
Category : Electronic
ISBN : NASA:31769000458862
Author : James N. Mueller,John E. Grimaud
Publisher : Unknown
Page : 72 pages
File Size : 43,8 Mb
Release : 1959
Category : Aerodynamic load
ISBN : UIUC:30112106564153
Author : Harry W. Carlson
Publisher : Unknown
Page : 38 pages
File Size : 46,9 Mb
Release : 1960
Category : Aerodynamic load
ISBN : UIUC:30112106569848
Author : Marlowe D. Cassetti,Richard J. Re,William B. Igoe
Publisher : Unknown
Page : 104 pages
File Size : 42,6 Mb
Release : 1961
Category : Transonic wind tunnels
ISBN : UIUC:30112106914986
An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Author : Wilbur D. Middleton
Publisher : Unknown
Page : 32 pages
File Size : 49,7 Mb
Release : 1963
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106874305
Author : Samuel M. Dollyhigh
Publisher : Unknown
Page : 126 pages
File Size : 40,5 Mb
Release : 1971
Category : Aerodynamics
ISBN : UIUC:30112106693176
An experimental investigation was made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60 deg leading-edge-sweep wing; however, a small amount of data were obtained for a 44 deg leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard. Further, this interference decreased somewhat with increasing Mach number. Raising the canard above the plane of the wing also greatly decreased the interference of the canard deflection on the wing lift. However, at Mach 2.86 the presence of the canard in the high position had a greater unfavorable interference effect at high angles of attack than the canard in the wing plane. This interference resulted in the in-plane canard having better trimmed performance at Mach 2.86 for the same center-of-gravity location.
Author : William B. Igoe,Richard J. Re,Maarlowe D. Cassetti
Publisher : Unknown
Page : 56 pages
File Size : 54,5 Mb
Release : 1961
Category : Aerodynamics
ISBN : UIUC:30112106590380
Author : Robert J. Mack
Publisher : Unknown
Page : 56 pages
File Size : 53,5 Mb
Release : 1974
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106913244
Wing models were tested in the high-speed section of the Langley Unitary Plan wind tunnel to study the effects of the leading-edge sweep angle and the design lift coefficient on aerodynamic performance and efficiency. The models had leading-edge sweep angles of 69.44 deg, 72.65 deg, and 75.96 deg which correspond to values of the design Mach-number-sweep-angle parameter (beta cotangent A) sub DES of 0.6, 0.75, and 0.9, respectively. For each sweep angle, camber surfaces having design lift coefficients of 0,0.08, and 0.12 at a design Mach number of 2.6 were generated. The wind-tunnel tests were conducted at Mach numbers of 2.3, 2.6, and 2.96 with a stagnation temperature of 338.7 K (150 F) and a Reynolds number per meter of 9.843 times 10 to the 6th power. The results of the tests showed that only a moderate sweeping of the wing leading edge aft of the Mach line along with a small-to-moderate amount of camber and twist was needed to significantly improve the zero-lift (flat camber surface) wing performance and efficiency.
Author : W. F. Lindsey
Publisher : Unknown
Page : 24 pages
File Size : 48,5 Mb
Release : 1954
Category : Aerodynamics
ISBN : UOM:39015086465567
Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.