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Wind Tunnel Force Measurements On A 05 Scale Model Of Black Arrow At Mach Numbers Of 12 15 And 20
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Book Synopsis Wind-tunnel Force Measurements on a .05 Scale Model of Black Arrow at Mach Numbers of 1.2, 1.5 and 2.0 by : J. R. Hall
Download or read book Wind-tunnel Force Measurements on a .05 Scale Model of Black Arrow at Mach Numbers of 1.2, 1.5 and 2.0 written by J. R. Hall and published by . This book was released on 1973 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Force Measurements on a 1/20 Scale Model of Black Arrow at Mach Numbers of 1.2, 1.5 and 2.0 by : J. R. Hall
Download or read book Wind-tunnel Force Measurements on a 1/20 Scale Model of Black Arrow at Mach Numbers of 1.2, 1.5 and 2.0 written by J. R. Hall and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1974 with total page 992 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1.5 to 19.5 by : C. J. Schueler
Download or read book An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1.5 to 19.5 written by C. J. Schueler and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the test section flow blockage characteristics was conducted in the 12- by 12 inch supersonic wind tunnel (Tunnel E-1) of the Von Karman Gas Dynamics Facility (AEDC). The purpose of the tests was to determine whether a method of predicting the maximum size model which will permit the establishment of supersonic flow, based on the model frontal area and bow shock-wave strength, is applicable over a wide range of Mach numbers. The tests conducted over the Mach number range from 1.5 to 5 using test models consisting of 15, 20, and 20 degrees half-angle cones, cone-cylinder combinations, and a series of discs. The inadequacy of the one dimensional, normal shock theory for predicting allowable model sizes was reconfirmed in these tests. Furthermore a correlation based on shock wave strength and model frontal area was found to be suitable only over a limited range of Mach numbers. Permissible hemisphere-cylinder model sizes from several wind tunnels covering the Mach number range from 1.5 to 19.5 are also presented.
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 0.60 to 1.20 of the Static Aerodynamic Characteristics of a Model of a Possible Nonlifting Reentry Capsule in Combination with a Rocket Booster by : Albin O. Pearson
Download or read book Wind-tunnel Investigation at Mach Numbers from 0.60 to 1.20 of the Static Aerodynamic Characteristics of a Model of a Possible Nonlifting Reentry Capsule in Combination with a Rocket Booster written by Albin O. Pearson and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Index written by and published by . This book was released on 1975 with total page 1262 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Measurements of Aerodynamic Damping Derivatives of a Launch Vehicle Vibrating in Free-free Bending Modes at Mach Numbers from 0.70 to 2.87 and Comparisons with Theory by : Perry W. Hanson
Download or read book Wind Tunnel Measurements of Aerodynamic Damping Derivatives of a Launch Vehicle Vibrating in Free-free Bending Modes at Mach Numbers from 0.70 to 2.87 and Comparisons with Theory written by Perry W. Hanson and published by . This book was released on 1962 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Force Measurements on Axisymmetric Models with Hammerhead Noses at Transonic Speeds by : Bruno J. Gambucci
Download or read book Force Measurements on Axisymmetric Models with Hammerhead Noses at Transonic Speeds written by Bruno J. Gambucci and published by . This book was released on 1967 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Tests of Rectangular Finned Variable Gap Tangent Ogive-cylinder Model at Mach Numbers 1.75 to 4.50 by : Neil Arthur Zarin
Download or read book Wind Tunnel Tests of Rectangular Finned Variable Gap Tangent Ogive-cylinder Model at Mach Numbers 1.75 to 4.50 written by Neil Arthur Zarin and published by . This book was released on 1964 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Longitudinal Airplane Dynamics Wind Tunnel Test Equipment by : O. B. Tufts
Download or read book Longitudinal Airplane Dynamics Wind Tunnel Test Equipment written by O. B. Tufts and published by . This book was released on 1955 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel/flight Data Correlation (u). by : James A. Behal
Download or read book Wind Tunnel/flight Data Correlation (u). written by James A. Behal and published by . This book was released on 1971 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Book Synopsis U.S. Government Research & Development Reports by :
Download or read book U.S. Government Research & Development Reports written by and published by . This book was released on 1968 with total page 840 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Force and Moment Measurements on a Number of Possible Re-entry Shapes at Mach Numbers 1.4 to 4.38 by : F. E. Deudney
Download or read book Wind Tunnel Force and Moment Measurements on a Number of Possible Re-entry Shapes at Mach Numbers 1.4 to 4.38 written by F. E. Deudney and published by . This book was released on 1960 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis CFD Wing/pylon/finned Store Mutual Interference Wind Tunnel Experiment by : E. Rolland Heim
Download or read book CFD Wing/pylon/finned Store Mutual Interference Wind Tunnel Experiment written by E. Rolland Heim and published by . This book was released on 1991 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Method to Calculate Uncertainties of Drag Coefficient Wind Tunnel Data by : Spence E. Peters (Jr.)
Download or read book A Method to Calculate Uncertainties of Drag Coefficient Wind Tunnel Data written by Spence E. Peters (Jr.) and published by . This book was released on 1980 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft by : J. F. Herman
Download or read book Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft written by J. F. Herman and published by . This book was released on 1979 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Measurements of Total Force and Extremity Flail Potential Forces on a Crew Member in Close Proximity to a Cockpit by : Harold L. Newhouse
Download or read book Wind Tunnel Measurements of Total Force and Extremity Flail Potential Forces on a Crew Member in Close Proximity to a Cockpit written by Harold L. Newhouse and published by . This book was released on 1980 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: In order to determine the aerodynamic forces acting upon a crew member/escape seat combination at transonic speeds, and the flail potential forces acting on the crewmember's extremities, an existing half scale man/seat combination was integrated with a model of the forward portion of the F-16. The combination was tested in the Arnold Engineering Development Center Propulsion Wind Tunnel (PWT) Facility Transonic Wind Tunnel (16T) during the period September 9 to September 15, 1978, over the Mach number range 0.4 to 1.2. The basic data obtained in this way are reported in Reichenau. The present report describes the experimental set-up in detail and presents some typical force and force area (force/sq. q) plots. From earlier work it was determined that the flow over the model was 'supercritical', implying a turbulent boundary layer at separation, and a reasonably realistic simulation of full-scale conditions. Very marked interference effects were observed on the man/seat combination, due to fuselage proximity. The most dramatic were large increases in upper arm and upper leg flail potential forces. In almost all cases, the most severe interference occurred when a 'flow diverter' was mounted in front of the cockpit. Comparisons with other sources of data revealed generally good agreement, except that the drag of the model was somewhat low; presumably due to the fact that the model was smoother than its full scale equivalent.
