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Book Wind Tunnel Tests of 5 Scale Vertical Ramp and Semi conical A3J 1 Inlet Models at Mach Numbers of 1 61 1 80 and 2 05

Download or read book Wind Tunnel Tests of 5 Scale Vertical Ramp and Semi conical A3J 1 Inlet Models at Mach Numbers of 1 61 1 80 and 2 05 written by Marion R. Bottorff and published by . This book was released on 1956 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind Tunnel Tests of a 5 Scale Semi conical A3J 1 Inlet Model at Mach Numbers of 0 9 1 2 1 4 1 6 1 8 and 2 05

Download or read book Wind Tunnel Tests of a 5 Scale Semi conical A3J 1 Inlet Model at Mach Numbers of 0 9 1 2 1 4 1 6 1 8 and 2 05 written by Marion R. Bottorff and published by . This book was released on 1957 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind Tunnel Tests of Two dimensional and Half axisymmetric Inlet Models at Mach Numbers 1 5 Through 3 0

Download or read book Wind Tunnel Tests of Two dimensional and Half axisymmetric Inlet Models at Mach Numbers 1 5 Through 3 0 written by Frederick K. Hube and published by . This book was released on 1970 with total page 278 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book One fifth Scale Inlet Model Wind Tunnel Test Report

Download or read book One fifth Scale Inlet Model Wind Tunnel Test Report written by GENERAL ELECTRIC CO CINCINNATI OHIO ADVANCED ENGINE AND TECHNOLOGY Dept and published by . This book was released on 1965 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tabulated data are presented for the high speed tests (Mach 0.4 to 0.85).

Book Wind Tunnel flight Data Correlation u

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 1104 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 Wind Tunnel flight Data Correlation u

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 656 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 Wind Tunnel Investigation of a 1 9 scale Boeing Company Amsa Airplane inlet Model at Transonic and Supersonic Mach Numbers

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 One fifth Scale Inlet Model Wind Tunnel Test Report

Download or read book One fifth Scale Inlet Model Wind Tunnel Test Report written by GENERAL ELECTRIC CO CINCINNATI OHIO ADVANCED ENGINE AND TECHNOLOGY Dept and published by . This book was released on 1965 with total page 610 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tabulated data are presented for the low speed tests (Mach 0 to 0.2).

Book Wind Tunnel Tests of a Two Thirds Scale NASA HRE Inlet at Mach Numbers 4 5 6 and 8

Download or read book Wind Tunnel Tests of a Two Thirds Scale NASA HRE Inlet at Mach Numbers 4 5 6 and 8 written by Frederick K. Hube and published by . This book was released on 1969 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: An axisymmetric, variable geometry, two-thirds scale model of a NASA Hypersonic Research Engine (HRE) inlet was tested at Mach numbers 4, 5, 6, and 8. Surface pressures and temperatures were measured on the inlet centerbody and inside the cowl. Pitot pressure measurements were made at four stations along the internal passage. The measurements were obtained for various cowl positions at free-stream Reynolds numbers from 1.08 to 5.76 million (based on a 12-in. cowl diameter) and over an angle-of-attack range from -5 to +5 deg. The model walls were internally cooled and maintained at a minimum frost-free condition at each test condition. Selected results are presented to illustrate the effects of cowl position, angle of attack, Mach number, and Reynolds number on the surface and rake station measurements. Inlet performance data at design operating conditions are also presented. (Author).

Book Wind Tunnel Tests of a Two Thirds Scale NASA HRE Inlet at Mach Numbers 4 5 6 and 8

Download or read book Wind Tunnel Tests of a Two Thirds Scale NASA HRE Inlet at Mach Numbers 4 5 6 and 8 written by and published by . This book was released on 1969 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An axisymmetric, variable geometry, two-thirds scale model of a NASA Hypersonic Research Engine (HRE) inlet was tested at Mach numbers 4, 5, 6, and 8. Surface pressures and temperatures were measured on the inlet centerbody and inside the cowl. Pitot pressure measurements were made at four stations along the internal passage. The measurements were obtained for various cowl positions at free-stream Reynolds numbers from 1.08 to 5.76 million (based on a 12-in. cowl diameter) and over an angle-of-attack range from -5 to +5 deg. The model walls were internally cooled and maintained at a minimum frost-free condition at each test condition. Selected results are presented to illustrate the effects of cowl position, angle of attack, Mach number, and Reynolds number on the surface and rake station measurements. Inlet performance data at design operating conditions are also presented. (Author).

Book One fifth Scale Inlet Model Wind Tunnel Test Report

Download or read book One fifth Scale Inlet Model Wind Tunnel Test Report written by GENERAL ELECTRIC CO CINCINNATI OHIO ADVANCED ENGINE AND TECHNOLOGY Dept and published by . This book was released on 1965 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary tables, graphs, model description, instrumentation, conditions tested, validity of data and other information are presented.