Download or read book Flight Investigation of the Supersonic Area Rule for a Straight Wing body Configuration at Mach Numbers Between 0 8 and 1 5 written by Sherwood Hoffman and published by . This book was released on 1955 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Flight Investigation of the Transonic Area Rule for a 52 5 Sweptback Wind body Configuration at Mach Numbers Between 0 8 and 1 6 written by Sherwood Hoffman and published by . This book was released on 1954 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic area rule Design and Rocket propelled Flight Investigation of a Zero lift Straight wing body nacelle Configuration Between Mach Numbers 0 8 and 1 53 written by Sherwood Hoffman and published by . This book was released on 1956 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The supersonic-area-rule concept was applied to the design of a straight-wing-body combination with large symmetrically mounted nacelles located at the 70-percent-semispan station. Both the nacelles and fuselage were indented to give a smooth total area distribution at a design Mach number of 1.41. The model was a zero-lift rocket-propelled vehicle and covered a continuous range of Mach number from 0.8 to 1.53 with corresponding Reynolds number from 3,000,000 to 4,000,000, based on wing mean aerodynamic chord. Also tested were two small equivalent bodies of revolution for Mach number 1.0 (which were propelled from a helium gun) of the basic wing-body combination.
Download or read book A Supersonic Area Rule and an Application to the Design of a Wing body Combination with High Lift drag Ratios written by Richard T. Whitcomb and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
Download or read book Supersonic area rule Design and Rocket propelled Flight Investigation of a Zero lift Straight wing body nacelle Configuration Between Mach Numbers 0 8 and 1 53 written by Sherwood Hoffman and published by . This book was released on 1956 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: The supersonic-area-rule concept was applied to the design of a straight-wing-body combination with large symmetrically mounted nacelles located at the 70-percent-semispan station. Both the nacelles and fuselage were indented to give a smooth total area distribution at a design Mach number of 1.41. The model was a zero-lift rocket-propelled vehicle and covered a continuous range of Mach number from 0.8 to 1.53 with corresponding Reynolds number from 3,000,000 to 4,000,000, based on wing mean aerodynamic chord. Also tested were two small equivalent bodies of revolution for Mach number 1.0 (which were propelled from a helium gun) of the basic wing-body combination.
Download or read book A Free flight Investigation of the Drag Coefficients of Two Single engine Supersonic Interceptor Configurations from Mach Number 0 8 to 1 90 to Determine the Effect of Inlet and Engine Locations written by Joseph H. Judd and published by . This book was released on 1955 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Preliminary Results of the Flight Investigation Between Mach Numbers of 0 80 and 1 36 of a Rocket powered Model of a Supersonic Airplane Configuration Having a Tapered Wing with Circular arc Sections and 40 Sweepback written by Charles T. D'Aiutolo and published by . This book was released on 1950 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation at Mach Numbers from 0 20 to 4 63 of the Aerodynamic Performance Static Stability and Trimming Characteristics of a Canard Configuration Designed for Efficient Supersonic Cruise Flight written by and published by . This book was released on 1961 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular arc Sections and a 40 Sweepback written by John P. Gapcynski and published by . This book was released on 1952 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Contractor Report written by and published by . This book was released on 1969 with total page 1366 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Investigation at Mach Number 1 92 of a Rectangular Wing and Tail and Body Configuration and Its Components written by Macon C. Ellis and published by . This book was released on 1950 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at Mach number 1.92 in the Langley 9-inch supersonic tunnel of a variable body-wing-tail configuration has been made in order to determine and to isolate the aerodynamic effects on each other of the components of the configuration.
Download or read book Some Examples of the Applications of the Transonic and Supersonic Area Rules to the Prediction of Wave Drag written by Robert L. Nelson and published by . This book was released on 1960 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of New Possibilities to Simplify the Standard Supersonic Area Rule written by V. R. Nikolic and published by . This book was released on 1983 with total page 101 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to find out whether there are possibilities to construct a procedure capable of giving reasonably accurate results for the aircraft wave drag coefficient over a range of Mach numbers or, at least, to predict the wave drag changes due to configuration changes. The idea was to build an algorithm starting from the standard supersonic area rule but employing different definitions for the area distribution along the longitudinal axis as applied to the equivalant body of revolution. Instead of using the set of planes tangent to the characteristic Mach cones, lateral surfaces of the cones were used. A computer program to perform the calculations following the procedure proposed was written. Several aircraft configurations were investigated by employing the developed method and very promising results for a particular type of supersonic aircraft configuration at moderate supersonic speeds were obtained. When applied to predict the wave drag of a configuration employing a thin wing of small aspect ratio centrally mounted on a slender fuselage at Mach numbers between 1.4 and 2.0, the method gave results within a range of ten percent accuracy.
Download or read book Preliminary In Flight Boundary Layer Transition Measurements on a 45 Deg Swept Wing at Mach Numbers Between 0 9 and 1 8 written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-10-25 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: A preliminary flight experiment was flown to generate a full-scale supersonic data base to aid the assessment of computational codes, to improve instrumentation for measuring boundary layer transition at supersonic speeds, and to provide preliminary information for the definition of follow-on programs. The experiment was conducted using an F-15 aircraft modified with a small cleanup test section on the right wing. Results are presented for Mach (M) numbers from 0.9 to 1.8 at altitudes from 25,000 to 55,000 ft. At M greater than or = 1.2, transition occurred near or at the leading edge for the clean configuration. The furthest aft that transition was measured was 20 percent chord at M = 0.9 and M = 0.97. No change in transition location was observed after the addition of a notch-bump on the leading edge of the inboard side of the test section which was intended to minimize attachment line transition problems. Some flow visualization was attempted during the flight experiment with both subliming chemicals and liquid crystals. However, difficulties arose from the limited time the test aircraft was able to hold test conditions and the difficulty of positioning the photo chase aircraft during supersonic test points. Therefore, no supersonic transition results were obtained. Johnson, J. Blair Armstrong Flight Research Center RTOP 533-02-21...
Download or read book A Supersonic Area Rule and an Application to the Design of a Wing body Combination with High Lift drag Ratios written by Richard T. Whitcomb and published by . This book was released on 1960 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
Download or read book An Investigation of the Transonic Area Rule by Flight Tests of a Sweptback Wing on a Cylindrical Body with and Without Body Indentation Between Mach Numbers 0 9 and 1 8 written by Sherwood Hoffman and published by . This book was released on 1953 with total page 24 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.
