Download or read book Aerodynamic Characteristics of Several Airfoils of Low Aspect Ratio written by Charles Horton Zimmerman and published by . This book was released on 1935 with total page 530 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Ground Proximity on the Aerodynamic Characteristics of Aspect ratio 1 Airfoils with and Without End Plates written by Arthur W. Carter and published by . This book was released on 1961 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made to determine the effect of ground proximity on the aerodynamic characteristics of aspect-ratio-1 airfoils. The investigation was made with the model moving over the water in a towing tank in order to eliminate the effects of wind-tunnel walls and of boundary layer on ground boards at small ground clearances. The results indicated that, as the ground was approached, the airfoils experienced an increase in lift-curve slope and a reduction in induced drag thus, lift-drag ratio was increased. As the ground was approached, the profile drag remained essentially constant for each airfoil. Near the ground, the addition of end plates to the airfoil resulted in a large increase in lift-drag ratio. The lift characteristics of the airfoils indicated stability of height at positive angles of attack and instability of height at negative angles; therefore, the operating range of angles of attack would be limited to positive values. At positive angles of attack, the static longitudinal stability was increased as the height above the ground was reduced. Comparison of the experimental data with Wieselsberger's ground-effect theory (NACA Technical Memorandum 77) indicated generally good agreement between experiment and theory for the airfoils without end plates.

Download or read book Aerodynamic Characteristics of a Large Number of Airfoils Tested in the Variable density Wind Tunnel written by Isadore Edward Garrick and published by . This book was released on 1938 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Aerodynamic Characteristics of Three Tapered Airfoils Tested in the Variable Density Wind Tunnel written by Raymond F. Anderson and published by . This book was released on 1931 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains the lift, drag, and moment characteristics of tapered Clark Y, Gottingen 398, and U.S.A. 45 airfoils as obtained from tests made in the Variable Density Wind Tunnel. The results are given at both low and high Reynolds numbers to show scale effect and to provide data for use in airplane design.

Download or read book Transonic Wind tunnel Investigation of the Effects of Aspect Ratio Spanwise Variations in Section Thickness Ratio and a Body Indentation on the Aerodynamic Characteristics of a 45 Sweptback Wing body Combination written by Melvin M. Carmel and published by . This book was released on 1953 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental and Calculated Characteristics of Several High aspect ratio Tapered Wings Incorporated NACA 44 series 230 series and Low drag 64 series Airfoil Sections written by Thomas V. Bollech and published by . This book was released on 1948 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt: Contains a comparison of the theoretical and experimental aerodynamic characteristics of three wings having similar plan forms and root- and tip-chord thickness ratios with aspect ratio of 10, taper ratio 2.5. The airfoil sections incorporated in the wings were the NACA 44-series, 64-series, and 230-series. The results show the effects of airfoil section on the characteristics of tapered wings for an approximate Reynolds number range of 2,000,000 to 5,000,000.

Download or read book Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees Aspect Ratio 4 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.

Download or read book Experimental and Theoretical Studies of the Effects of Camber and Twist on the Aerodynamic Characteristics of Parawings Having Normal Aspect Ratios of 3 and 6 written by Edward Charles Polhamus and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Low-speed wind-tunnel studies were made of the effects of camber and twist and the effects of aspect ratio on the aerodynamic characteristics of parawings. To determine the effects of camber and twist, tests were made both with the conventional conical-type canopy, which provides camber and washout, and with a cylindrical-type canopy which provides essentially zero camber and twist. With regard to aspect ratio, tests were made of parawings having aspect ratios of 3 and 6; the range was thereby extended well beyond that of previous investigations. The degree to which airfoil and wing theory can be used to predict the aerodynamic characteristics of parawings was also investigated.

Download or read book Aerodynamic Characteristics of a Wing with Unswept Quarter chord Line Aspect Ratio 2 Taper Ratio 0 78 and NACA 65A004 Airfoil Section written by Edward C. Polhamus and published by . This book was released on 1950 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of a low-aspect-ratio wing have been investigated in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.60 to 1.17 by use of the transonic bump technique. The results include lift, drag, pitching-moment, and root bending moment for a wing having an unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and an NACA 65A004 airfoil section.

Download or read book Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils from Tests in the NACA Two dimensional Low turbulence Pressure Tunnel written by Albert E. Von Doenhoff and published by . This book was released on 1944 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Two low-drag airfoils, the NACA 747A315 and the NACA 747A415, designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient have been tested in the NACA two-dimensional low-turbulence pressure tunnel. Section lift, drag, and pitching-moment coefficients are presented for Reynolds numbers of 3 x 106, 6 x 106, and 9 x 106, together with section lift and section drag data for a Reynolds number of 6 x 106 for the same airfoils with roughened leading edges.

Download or read book Full scale Investigation of the Aerodynamic Characteristics of a Model Employing a Sailwing Concept written by Marvin P. Fink and published by . This book was released on 1967 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley full-scale tunnel to determine the aerodynamic characteristics of a full-scale model employing a sailwing concept and having a wing aspect ratio of 11.5. The wing had a rigid leading-edge spar, rigid root and wing-tip ribs with a trailing-edge stretched between these ribs, and a fabric covering stretched between the leading and trailing edeges. The fabric of the sail maintained a smooth airfoil contour over the installed angle-of-attack range, but some rippling occurred at the trailing edge near the wing root as the wing stalled. The aerodynamic characteristics of the sailwing, in particular the maximum lift and maximum lift-drag ratio, compared favorably with those of conventional hard wings. A lateral-control device based on the wing-warp principle was effective at angles of attack below that for wing stall, but at angles near stall, the control effectiveness became low and nonlinear.

Download or read book The Aerodynamic Characteristics of Seven Frequently Used Wing Sections at Full Reynolds Number written by Walter Stuart Diehl and published by . This book was released on 1926 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of Several 6 percent thick Airfoils at Angles of Attack from 0 to 20 Degrees at High Subsonic Speeds written by Bernard N. Daley and published by . This book was released on 1949 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-dimensional tests of eight 6-percent-thick symmetrical airfoils of the supersonic and subsonic types were conducted in the Langley rectangular high-speed tunnel. The aerodynamic characteristics of each of the airfoils have been determined from the measured pressure data. These results showed that the lift-curve slope of each of the airfoils decreased rapidly to a positive value approaching zero at angles of attack near 9 degrees and roughly maintained this value up to the highest angle of attack tested.

Download or read book The Aerodynamic Characteristics of an Aspect ratio 20 Wing Having Thick Airfoil Sections and Employing Boundary layer Control by Suction written by Bennie W. Cocke and published by . This book was released on 1953 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted to study the aerodynamic characteristics of an aspect-ration-20 wing having thick airfoil sections and employing boundary-layer control by suction. Data from model tests in both the Langley full-scale tunnel and the Langley low-turbulence pressure tunnels are included. The results indicate the effects of varying suction flow rate, suctioin-slot configurations, wing surface condition, flap deflection, and Mach number.

Download or read book The Effect of Small Variations in Profile of Airfoils written by Kenneth E. Ward and published by . This book was released on 1931 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: These tests show that small changes in airfoil contours, resulting from variations in the specified ordinates, have a sufficiently large effect upon the airfoil characteristics to justify the taking of great care in the specification of ordinates for the construction of models.

Download or read book Aerodynamic Characteristics at Small Scale and a Mach Number of 1 38 of Untapered Wings Having M and W Plan Forms written by William B. Kemp and published by . This book was released on 1954 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low speed Longitudinal Aerodynamic Characteristics Associated with a Series of Low aspect ratio Wings Having Variations in Leading edge Contour written by Bernard Spencer and published by . This book was released on 1962 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: