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Wind Tunnel Investigation Of A 1 9 Scale Boeing Company Amsa Airplane Inlet Model At Transonic And Supersonic Mach Numbers
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Book Synopsis Wind Tunnel Investigation of a 1/9-scale Boeing Company Amsa Airplane-inlet Model at Transonic and Supersonic Mach Numbers by :
Download or read book Wind Tunnel Investigation of a 1/9-scale Boeing Company Amsa Airplane-inlet Model at Transonic and Supersonic Mach Numbers written by and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 1/9-scale model of the AMSA was tested in the Propulsion Wind Tunnel, Transonic (16T) and Propulsion Wind Tunnel, Supersonic (16S) of the Propulsion Wind Tunnel Facility (PWT). The test vehicle consisted of an airplane model and two pressure-instrumented inlet nacelles. Airplane model variations representing three-engine and four-engine configurations were tested with the two engine nacelles representing either two-thirds or one-half of the full airplane configuration. The three-engine configuration consisted of one pylon-mounted nacelle under the left wing and one tail-mounted nacelle above the fuselage on the airplane vertical centerline. The symmetrical four-engine configurations had either two adjacent nacelles suspended under the left wing or one forward nacelle under the left wing and one nacelle mounted aft on the left side of the fuselage near the tail. Data were obtained at free-stream Mach numbers from 0.60 to 2.30 to determine the performance characteristics of the inlets, and the effects of mutual interactions of inlets and airplane surfaces. The model attitude was varied throughout an angle-of-attack range of -4 to +11 deg and yaw angles of plus or minus 4 deg.
Book Synopsis Wind Tunnel Investigation of a 1/9-scale Boeing Company Amsa Airplane-inlet Model at Transonic and Supersonic Mach Numbers by : D. C. Baker
Download or read book Wind Tunnel Investigation of a 1/9-scale Boeing Company Amsa Airplane-inlet Model at Transonic and Supersonic Mach Numbers written by D. C. Baker and published by . This book was released on 1967 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 1/9-scale model of the AMSA was tested in the Propulsion Wind Tunnel, Transonic (16T) and Propulsion Wind Tunnel, Supersonic (16S) of the Propulsion Wind Tunnel Facility (PWT). The test vehicle consisted of an airplane model and two pressure-instrumented inlet nacelles. Airplane model variations representing three-engine and four-engine configurations were tested with the two engine nacelles representing either two-thirds or one-half of the full airplane configuration. The three-engine configuration consisted of one pylon-mounted nacelle under the left wing and one tail-mounted nacelle above the fuselage on the airplane vertical centerline. The symmetrical four-engine configurations had either two adjacent nacelles suspended under the left wing or one forward nacelle under the left wing and one nacelle mounted aft on the left side of the fuselage near the tail. Data were obtained at free-stream Mach numbers from 0.60 to 2.30 to determine the performance characteristics of the inlets, and the effects of mutual interactions of inlets and airplane surfaces. The model attitude was varied throughout an angle-of-attack range of -4 to +11 deg and yaw angles of plus or minus 4 deg.
Book Synopsis Wind Tunnel Investigation of a 1/8-Scale AMSA Aircraft-Inlet Model at Transonic and Supersonic Mach Numbers by : Lawrence L. Galigher
Download or read book Wind Tunnel Investigation of a 1/8-Scale AMSA Aircraft-Inlet Model at Transonic and Supersonic Mach Numbers written by Lawrence L. Galigher and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Test results are presented for a 1/8-scale inlet model of a proposed AMSA air induction system at transonic and supersonic Mach numbers. The effects of spike bleed pattern and inlet orientation are presented. Compressor-face total-pressure recovery and flow distortion data are presented as a function of spike position, compressor-face mass-flow ratio, spike boundary-layer bleed mass-flow ratio, angle of attack, angle of sideslip, and free-stream Mach number. (Author).
Book Synopsis Wind Tunnel Investigation of a 0.10-scale North American Aviation Amsa Inlet at Transonic and Supersonic Mach Numbers by : H. E. McDill
Download or read book Wind Tunnel Investigation of a 0.10-scale North American Aviation Amsa Inlet at Transonic and Supersonic Mach Numbers written by H. E. McDill and published by . This book was released on 1967 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Test results are presented for a study on a 0.10-scale model of the North American Aviation proposed advanced manned strategic aircraft air vehicle. Inlets of various geometries were tested at several Mach numbers, angles of attack, and angles of yaw. Inlet performance in terms of compressor face total-pressure recovery and flow distortion is presented as a function of mass-flow ratio for various inlet geometries at several Mach numbers and model attitudes. (Author).
Book Synopsis Wind Tunnel Investigation of a 0.10-scale North American Aviation Amsa Inlet at Transonic and Supersonic Mach Numbers by :
Download or read book Wind Tunnel Investigation of a 0.10-scale North American Aviation Amsa Inlet at Transonic and Supersonic Mach Numbers written by and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Test results are presented for a study on a 0.10-scale model of the North American Aviation proposed advanced manned strategic aircraft air vehicle. Inlets of various geometries were tested at several Mach numbers, angles of attack, and angles of yaw. Inlet performance in terms of compressor face total-pressure recovery and flow distortion is presented as a function of mass-flow ratio for various inlet geometries at several Mach numbers and model attitudes. (Author).
Book Synopsis Wind Tunnel Investigation of a 1/8 Scale AMSA Airpcraft-inlet Model at Transonic and Supersonic Mach Numbers by : Lawrence L. Galigher
Download or read book Wind Tunnel Investigation of a 1/8 Scale AMSA Airpcraft-inlet Model at Transonic and Supersonic Mach Numbers written by Lawrence L. Galigher and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Test results are presented for a 1/8-scale inlet model of a proposed AMSA air induction system at transonic and supersonic Mach numbers. The effects of spike bleed pattern and inlet orientation are presented. Compressor-face total-pressure recovery and flow distortion data are presented as a function of spike position, compressor-face mass-flow ratio, spike boundary-layer bleed mass-flow ratio, angle of attack, angle of sideslip, and free-stream Mach number. (Author).
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 850 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Notices of Changes in Classification, Distribution and Availability by :
Download or read book Notices of Changes in Classification, Distribution and Availability written by and published by . This book was released on 1977 with total page 428 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Data Base for the Prediction of Airframe/propulsion System Interference Effects by :
Download or read book Data Base for the Prediction of Airframe/propulsion System Interference Effects written by and published by . This book was released on 1979 with total page 444 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Results of 0.2-Scale B-1 Production Inlet Development and Verification Tests at Subsonic and Supersonic Mach Numbers by :
Download or read book Results of 0.2-Scale B-1 Production Inlet Development and Verification Tests at Subsonic and Supersonic Mach Numbers written by and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for a wind tunnel investigation of the 0.2- scale B-1 aircraft inlet/forebody model during which a production version of the inlet configuration was defined and the performance characteristics verified. The test was conducted at Mach numbers from 0 to 2.3, at angles of attack from - 2 to 13 deg, and at yaw angles from -6 to 6 deg. Performance data are presented primarily in the form of engine-face total-pressure recovery, turbulence index, and various distortion indices as a function of engine-face mass-flow ratio. For the development test phase, results are given that show the effects of reducing the inlet diffuser ramp length, varying the inlet cowl lip contours, changing the inlet bleed porosities, and reducing the inlet bleed discharge area. The performance characteristics of the selected inlet configuration are documented over the Mach number range with inlet geometry as controlled by the individual inlet control sensor schedules as well as by a free-stream Mach number schedule. The effects of control system errors and the aircraft takeoff inlet performance characteristics are also presented.
Book Synopsis Government Reports Announcements & Index by :
Download or read book Government Reports Announcements & Index written by and published by . This book was released on 1977 with total page 1116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Inlet Performance Characteristics of a Generalized 1/5.2-Scale Aircraft Model at Transonic and Supersonic Mach Numbers by :
Download or read book Inlet Performance Characteristics of a Generalized 1/5.2-Scale Aircraft Model at Transonic and Supersonic Mach Numbers written by and published by . This book was released on 1976 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel investigation was conducted at free-stream Mach numbers from 0.55 to 2.0 on a 1/5.2-scale composite inlet model to evaluate configuration factors which affected inlet performance. In addition, flow-field surveys were made at the inlet throat and on the fuselage, forward of the inlet cowl lip. Inlet performance parameters in terms of total-pressure recovery, distortion, and turbulence at the simulated compressor face, as well as compressor face and throat station total-pressure contours and diffuser duct static-pressure distributions are presented for various Mach numbers and angles of attack and sideslip. The basic air induction system consisted of a normal-shock-type inlet with a long splitter plate assembly and was located beneath the wing glove in proximity to the fuselage. The total-pressure recovery for the basic inlet system was slightly better than normal shock recovery for cruise attitudes at supersonic Mach numbers. At Mach numbers approaching 2.0, the basic inlet system was operating close to the buzz limit at design engine airflow. Reductions in total-pressure distortion were achieved by increasing the fuselage-to-inlet standoff distance and by inlet duct boundary-layer blowing. (Author).
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722915704 Total Pages :184 pages Book Rating :4.9/5 (157 download)
Book Synopsis A Wind Tunnel Investigation of Three NACA 1-Series Inlets at Mach Numbers Up To 0. 92 by : National Aeronautics and Space Administration (NASA)
Download or read book A Wind Tunnel Investigation of Three NACA 1-Series Inlets at Mach Numbers Up To 0. 92 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 184 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions on three NACA 1-series inlets have been obtained in the Langley 16-Foot Transonic Tunnel. The cowl diameter ratio (ratio of cowl highlight diameter to cowl maximum diameter) was 0.85 for all three inlets. The cowl length ratio (ratio of cowl length to cowl maximum diameter) was 1.0 for two of the inlets (NACA 1-85-100) and 0.439 for the other (NACA 1-85-43.9) inlet. One of the inlets with a cowl length ratio of 1.0 had an internal contraction ratio (ratio of highlight area to throat area) of 1.009 and the other had a contraction ratio of 1.250. The inlet with a cowl length ratio of 0.439 also had an internal contraction ratio of 1.250. All three inlets had longitudinal rows of static pressure orifices on the top and bottom external cowl surfaces. The inlet with a contraction ratio of 1.009 also had a row of static pressure orifices on the side of the cowl (external surface). The two inlets with a contraction ratio of 1.250 had a longitudinal row of static pressure orifices on the diffuser surface. Re, Richard J. and Abeyounis, William K. Langley Research Center WIND TUNNEL TESTS; PRESSURE DISTRIBUTION; STATIC PRESSURE; ENGINE INLETS; AIRCRAFT ENGINES; MACH NUMBER; ANGLE OF ATTACK; SUBSONIC FLOW; CONTRACTION; NACELLES; FOREBODIES; MASS FLOW; PRESSURE MEASUREMENT; AXISYMMETRIC BODIES...
Book Synopsis Large-scale Wind-tunnel Investigation of a Model with an External Jet-augmented Flap by : Jerry V. Kirk
Download or read book Large-scale Wind-tunnel Investigation of a Model with an External Jet-augmented Flap written by Jerry V. Kirk and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Annual Index by :
Download or read book Government Reports Annual Index written by and published by . This book was released on 1977 with total page 1108 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 Wind Tunnel Investigation of the Interaction and Breakdown Characteristics of Slender-wing Vortices at Subsonic, Transonic, and Supersonic Speeds by : Gary E. Erickson
Download or read book Wind Tunnel Investigation of the Interaction and Breakdown Characteristics of Slender-wing Vortices at Subsonic, Transonic, and Supersonic Speeds written by Gary E. Erickson and published by . This book was released on 1991 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt:
