Download or read book Influence of Leading edge Suction on Lift drag Ratios of Wings at Supersonic Speeds written by Clarence B. Cohen and published by . This book was released on 1948 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: The possible gain in lift-drag ratio for region of wing affected by tip increases as the sweepback of wing is increased. An appropriately curved tip gives higher lift-drag ratios than the best trapezoidal tip.
Download or read book Effect of Leading edge Sweepback on Lift Drag and Pitching moment Characteristics of Thin Wings of Aspect Ratio 3 and Taper Ratio 0 4 at Subsonic and Supersonic Speeds written by Benton E. Wetzel and published by . This book was released on 1955 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Factors Affecting the Maximum Lift drag Ratio at High Supersonic Speeds written by Charles H. McLellan and published by . This book was released on 1956 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study of the factors affecting the maximum lift-drag ratio has been conducted in an effort to determine how to obtain high aerodynamic values at high supersonic Mach numbers.
Download or read book Drag Due to Lift at Mach Numbers Up to 2 0 written by Edward C. Polhamus and published by . This book was released on 1953 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Studies of Various Factors Affecting Drag Due to Lift at Subsonic Speeds written by William P. Henderson and published by . This book was released on 1966 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by Ross B. Robinson and published by . This book was released on 1952 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical and Experimental Longitudinal Aerodynamic Characteristics of an Aspect Ratio 0 25 Sharp edge Delta Wing at Subsonic Supersonic and Hypersonic Speeds written by Charles H. Fox and published by . This book was released on 1974 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The suction analogy concept of Polhamus for predicting vortex lift in conjunction with an appropriate potential-flow solution is called the present method. This method is applied herein to an aspect ratio of 0.25 sharp-edge delta wing from a Mach number of 0.143 to 10.4 in free air and at 0.074 in ground effect, and also to an aspect ratio of 0.35 triangular cross-sectional body at Mach number of 6.9. The models had subsonic leading edges at the test Mach numbers. Vortex-flow effects could be neither confirmed nor denied to exist at high speeds because of the lack of flow visualization above a Mach number of 0.143. The data, however, could be better predicted by including a vortex-flow effect, although not always to the extent predicted from the present method because of the presence of actual and hypothesized unmodeled flow situations.
Download or read book Investigations at Supersonic Speeds of 22 Triangular Wings Representing Two Airfoil Sections for Each of 11 Apex Angles written by Eugene S. Love and published by . This book was released on 1949 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of tests of 11 triangular wings were conducted at Mach numbers 1.62, 1.92, and 2.40 to determine the effect of leading-edge shape and to compare actual test values with the nonviscous linear theory. The two series of wings had identical plan forms, a constant thickness ratio of 8 percent, a constant location of maximum-thickness point of 18 percent, and a range of apex half-angles from 10 to 45 degrees. The first series had an elliptical leading edge and the second series, a wedge leading edge. Measurements were made of lift, drag, pitching moment, and pressure distribution, the latter being confined to three wings at one Mach number.
Download or read book A Theoretical Investigation of the Aerodynamics of Wing tail Combinations Performing Time dependent Motions at Supersonic Speeds written by John C. Martin and published by . This book was released on 1954 with total page 720 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical investigation is presented of the contribution of horizontal tails to the lift and pitching moment due to angle of attack, a constant rate of pitch, and a constant vertical acceleration. Numerical values of the aerodynamic coefficients associated with these motions are presented for a number of two-dimensional wing-tail combinations, a triangular wing-tail combination, and a number of rectangular-wing - triangular-tail combinations.
Download or read book Effect of Taper Ratio on Lift Drag and Pitching moment Characteristics of Thin Wings of Aspect Ratio 3 with 53 1 Degree Sweepback of Leading Edge at Subsonic and Supersonic Speeds written by Benton E. Wetzel and published by . This book was released on 1955 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aircraft Configurations Developing High Lift drag Ratios at High Supersonic Speeds written by A. J. Eggers (Jr.) and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The problem of designing an aircraft which will develop high lift-drag ratios in flight at high supersonic speeds is attacked using the elementary principle that the components of the aircraft should be individually and collectively arranged to impart the maximum downward and the minimum forward momentum to the surrounding air. This principle in conjunction with other practical considerations of hypersonic flight leads to the study of configurations for which the body is situated entirely below the wing; that is, flat-top wing-body combinations. Theory indicates that sensibly complete aircraft of this type can be designed to develop lift-drag ratios well in excess of 6.
Download or read book Preliminary Investigation at Supersonic Speeds of Triangular and Sweptback Wings written by Macon C. Ellis and published by . This book was released on 1949 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results from a supersonic wind-tunnel investigation of a series of thin triangular and sweptback wings are presented. The triangular wing series consisted of eight triangular wings of vertex angles such that a range of leading-edge postions both inside and outside the Mach cone at the test Mach numbers of 1.43 and 1.71 was obtained. The three swept wings had angles of sweep at 45, 55, and 63 degrees and were tested at a Mach number of 1.43.
Download or read book Effect of a Finite Trailing edge Thickness on the Drag of Rectangular and Delta Wings at Supersonic Speeds written by E. B. Klunker and published by . This book was released on 1952 with total page 690 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of a finite trailing-edge thickness on the pressure drag of rectangular and delta wings with truncated diamond-shaped airfoil sections with a given thickness ratio is studied for supersonic Mach numbers, linearized theory being used to evaluate the surface pressures. In order to facilitate comparison with wings having sharp trailing edges, the position of maximum thickness and base height are determined for least thickness and base height are determined for least pressure drag as functions of a base-pressure parameter. Comparison is then made between the drag of these wings and similar wings with a sharp trailing edge for various aspect ratios and thickness ratios as a function of stream Mach number. The calculations of the drag characteristics for these wings show that significant drag characteristics for these wings show that significant drag reductions are possible under some condtions at high supersonic speeds. These reductions are relatively independent of aspect ratio for the rectangular wings but depend considerably on aspec ratio for the delta wings; the smaller aspect ratios show the larger drag reductions. Calculations of the spanwise distribution of drag are included to compare further the effect of a base on the drag fro different aspect ratios.
Download or read book Survey and Analysis of Research on Supersonic Drag due to lift Minimization with Recommendations for Wing Design written by Harry W. Carlson and published by . This book was released on 1992 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Wing Inboard Plan form Modifications on Lift Drag and Longitudinal Stability at Mach Numbers from 1 0 to 2 3 of a Rocket propelled Free flight Model with a 52 5 Degree Sweptback Wing of Aspect Ratio 3 written by Allen B. Henning and published by . This book was released on 1957 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made to determine the effects of wing inboard plan-form modifications on the lift, drag, and longitudinal characteristics of a rocket-propelled free-flight model. The model had a body of fineness ration 17.4, a modified wing with a basic plan form swept back 52.5 degrees and an aspect ratio of 3, and inline horizontal tail surfaces which were aerodynamically pulsed continuously throughout the flight.
Download or read book Studies Relating to the Attainment of High Lift drag Ratios at Hypersonic Speeds written by and published by . This book was released on 1965 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Note National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1948 with total page 876 pages. Available in PDF, EPUB and Kindle. Book excerpt:
