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Effects Of Distributed Roughness Height On Aerodynamic Characteristics And Boundary Layer Transition Of A Wing Body Tail Configuration At A Mach Number Of 161
Download Effects Of Distributed Roughness Height On Aerodynamic Characteristics And Boundary Layer Transition Of A Wing Body Tail Configuration At A Mach Number Of 161 full books in PDF, epub, and Kindle. Read online Effects Of Distributed Roughness Height On Aerodynamic Characteristics And Boundary Layer Transition Of A Wing Body Tail Configuration At A Mach Number Of 161 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Effects of Distributed Roughness Height on Aerodynamic Characteristics and Boundary-layer Transition of a Wing-body-tail Configuration at a Mach Number of 1.61 by : Roy V. Harris (Jr.)
Download or read book Effects of Distributed Roughness Height on Aerodynamic Characteristics and Boundary-layer Transition of a Wing-body-tail Configuration at a Mach Number of 1.61 written by Roy V. Harris (Jr.) and published by . This book was released on 1964 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Distributed Roughness Height on Aerodynamic Characteristics and Boundary-layer Transition of a Wing-body-tail Configuration at a Mach of 1.61 by : Roy V. Jr Harris
Download or read book Effects of Distributed Roughness Height on Aerodynamic Characteristics and Boundary-layer Transition of a Wing-body-tail Configuration at a Mach of 1.61 written by Roy V. Jr Harris and published by . This book was released on 1964 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on with total page 1958 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Simplified Method for Determination of Critical Height of Distributed Roughness for Boundary-layer Transition at Mach Numbers from 0 to 5 by : Albert L. Braslow
Download or read book Simplified Method for Determination of Critical Height of Distributed Roughness for Boundary-layer Transition at Mach Numbers from 0 to 5 written by Albert L. Braslow and published by . This book was released on 1958 with total page 624 pages. Available in PDF, EPUB and Kindle. Book excerpt: The method has been applied to various types of configurations in several wind-tunnel investigations conducted by the National Advisory Committee for Aeronautics at Mach numbers up to 4, and in all cases the calculated roughness height caused premature boundary-layer transition for the range of test conditions.
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 3.96 and 4.63 by : Maurice O. Feryn
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 3.96 and 4.63 written by Maurice O. Feryn and published by . This book was released on 1966 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 by : Royce L. McKinney
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 written by Royce L. McKinney and published by . This book was released on 1965 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Effects of Roughness, Surface Cooling, and Shock Impingement on Boundary-layer Transition on a Two-dimensional Wing by : K. R. Czarnecki
Download or read book Investigation of Effects of Roughness, Surface Cooling, and Shock Impingement on Boundary-layer Transition on a Two-dimensional Wing written by K. R. Czarnecki and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Vertical Location of Wing and Horizontal Tail on the Aerodynamic Characteristics in Pitch at Mach Numbers from 0.60 to 1.40 of an Airplane Configuration with an Unswept Wing by : Louis S. Stivers
Download or read book Effects of Vertical Location of Wing and Horizontal Tail on the Aerodynamic Characteristics in Pitch at Mach Numbers from 0.60 to 1.40 of an Airplane Configuration with an Unswept Wing written by Louis S. Stivers and published by . This book was released on 1957 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the effects of vertical location of an unswept wing and horizontal tail on the aerodynamic characteristics in pitch of a wing-body-tail combination. The wing had an aspect ratio of 3.09, a taper ratio of 0.39, and quarter-chord line swept back 11.5 degrees, and biconvex sections. Lift, drag, and pitching-moment coefficients were obtained at Mach numbers from 0.60 to 1.40 for angles of attack from -4 to approximately 13 degrees, with the boundary-layer transition on the model fixed and free. The Reynolds number of the tests was 1.5 million, based on the wing mean aerodynamic chord. The effects of Mach number on the experimental and calculated lift curve slopes, pitching-moment curve slopes, and contributions of the horizontal tail to the pitching-moment curve slopes are presented for the various wing and horizontal-tail locations.
Book Synopsis Effects of Wing and Tail Location on the Aerodynamic Characteristics of an Airplane for Mach Numbers from 0.25 to 4.63 by :
Download or read book Effects of Wing and Tail Location on the Aerodynamic Characteristics of an Airplane for Mach Numbers from 0.25 to 4.63 written by and published by . This book was released on 1983 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781725184299 Total Pages :34 pages Book Rating :4.1/5 (842 download)
Book Synopsis Effects of Wing and Tail Location on the Aerodynamic Characteristics of an Airplane for Mach Numbers from 0. 25 To 4. 63 by : National Aeronautics and Space Administration (NASA)
Download or read book Effects of Wing and Tail Location on the Aerodynamic Characteristics of an Airplane for Mach Numbers from 0. 25 To 4. 63 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-13 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental investigations have been conducted to determine the effect of wing vertical position and horizontal-tail vertical and axial position on the static aerodynamic characteristics of a wing-body horizontal-tail configuration. The configurations investigated included the wing in a high, mid, or low position on the body with the horizontal tail in each of these vertical positions as well as in three axial positions. The closest position of the horizontal tail to the wing essentially provided on all-wing configuration. In addition, tests were made for the three wing positions with the horizontal tail removed. The tests were made in three different wind tunnels to provide data for a Mach number range from 0.25 to 4.63. The purpose of the investigation was to illustrate the strong effects of interference flow fields as a function of geometry and flight regime. An analysis of the results indicate some arrangements that might lead to aerodynamic problems and others in which the interference flow fields might be favorably exploited. The results suggest that a coplanar concept with a translating horizontal tail could potentially minimize the aerodynamic changes with Mach number and provide more optimum performance over the Mach number range. Spearman, M. L. Langley Research Center NASA-TM-84643, NAS 1.15:84643 RTOP 505-43-43-01...
Book Synopsis Effectiveness of an All-movable Horizontal Tail on an Unswept-wing and Body Combination for Mach Numbers from 0.60 to 1.40 by : Louis S. Stivers
Download or read book Effectiveness of an All-movable Horizontal Tail on an Unswept-wing and Body Combination for Mach Numbers from 0.60 to 1.40 written by Louis S. Stivers and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Unit Reynolds Number, Nose Bluntness, and Roughness on Boundary Layer Transition by : J. Leith Potter
Download or read book Effects of Unit Reynolds Number, Nose Bluntness, and Roughness on Boundary Layer Transition written by J. Leith Potter and published by . This book was released on 1960 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: Condtions encountered in the high Mach number flow regime are show to profoundly affect the longitudinal extent of the boundary layer from beginning to end of transition, the distribution of fluctuation energy in the laminar layer, and effectiveness of surface roughness in promoting transition. A critical layer of intense local energy fluctuations was found at all Mach numbers studied. The existence of such a critical layer is predicted by stability theory. Hot-wire surveys of the laminar, transitional, and turbulent boundary layers are presented to illustrate the critical layer in laminar flow and subsequent development into the transition process. The relation between boundary layer transition on flat plates and cones in supersonic flow is explored and a process for correcting data to account for leading edge bluntness is devised. On the basis of a comparison of data corrected for the effects of leading edge geometry, it is shown that the Reynolds umber of transition on a cone is three times that on a vanishingly thin flate plate. Close agreement between data from various wind tunnels is demonstrated. Study of the effect of finite leading edges yields significant illustrations of the influence of unit Reynolds number on boundary layer transition. A correlation of the effects of surface roughness on transition is achieved. This treatment includes two- and three-dimensional roughness in both subsonic and supersonic streams. At this time only zero pressure gradients have been studied. The entire range of movement of transition from its position with no roughness up to its reaching the roughness element is describable by the procedure give. Examples of application of the correlation results show excellent agreement with experimental data from a variety of sources. Implications concerning tripping hypersonic boundary layers are discussed.
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 3.96 and 4.63 by :
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 3.96 and 4.63 written by and published by . This book was released on 1966 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 by :
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 written by and published by . This book was released on 1965 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations by : Harry W. Carlson
Download or read book An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations written by Harry W. Carlson and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: An experimental investigation has been performed to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and given longitudinal distribution of cross-sectional area but various cross-section shapes were tested at a Mach number of 2.01. The bodies were tested alone and in combination with a 47° sweptback wing having a 6-percent-thick hexagonal section.
Book Synopsis Aerodynamic Characteristics at Mach Numbers of 1.5, 1.8, and 2.0 of a Blended Wing-body Configuration with and Without Integral Canards by : A. Warner Robins
Download or read book Aerodynamic Characteristics at Mach Numbers of 1.5, 1.8, and 2.0 of a Blended Wing-body Configuration with and Without Integral Canards written by A. Warner Robins and published by . This book was released on 1979 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Investigation at Mach Number 1.92 of a Rectangular Wing and Tail and Body Configuration and Its Components by : Macon C. Ellis
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.
