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Book A Further Wind Tunnel Investigation of Underwing Jet Interference

Download or read book A Further Wind Tunnel Investigation of Underwing Jet Interference written by Arthur George Kurn and published by . This book was released on 1971 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind Tunnel Wall Interference January 1980 May 1988

Download or read book Wind Tunnel Wall Interference January 1980 May 1988 written by Marie H. Tuttle and published by . This book was released on 1988 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind tunnel Data from a 0 16 scale V STOL Model with Direct lift and Lift cruise Jets

Download or read book Wind tunnel Data from a 0 16 scale V STOL Model with Direct lift and Lift cruise Jets written by Matthew M. Winston and published by . This book was released on 1969 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book A Further Wind Tunnel Investigation of Underwing Jet Interference

Download or read book A Further Wind Tunnel Investigation of Underwing Jet Interference written by A. G. Kurn and published by . This book was released on 1969 with total page 49 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 Full Scale Subsonic Wind Tunnel Requirements and Design Studies

Download or read book Full Scale Subsonic Wind Tunnel Requirements and Design Studies written by Mark W. Kelly and published by . This book was released on 1972 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 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 Wall Interference in Wind Tunnels with Slotted and Porous Boundaries at Subsonic Speeds

Download or read book Wall Interference in Wind Tunnels with Slotted and Porous Boundaries at Subsonic Speeds written by Barrett Stone Baldwin and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Linearized compressible-flow analysis is applied to the study of wind-tunnel-wall interference for subsonic flow in either two-dimensional or circular test sections having slotted or porous walls. Expressions are developed for evaluating blockage and lift interference.

Book Wind Tunnel Results from a Nozzle Afterbody Test of A 0 1 Scale Fighter Aircraft in the Mach Number Regime of 0 6 to 1 6

Download or read book Wind Tunnel Results from a Nozzle Afterbody Test of A 0 1 Scale Fighter Aircraft in the Mach Number Regime of 0 6 to 1 6 written by Ernest J. Lucas and published by . This book was released on 1978 with total page 174 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to obtain throttle-dependent aft end drag on a one-tenth scale model of a twin-engine fighter aircraft (YF-17). These data will be used in assessing the validity of current wind tunnel data acquisition techniques. Pressure data were obtained for several configurations, using a wingtip support system, to define the effects of jet exhaust flow on afterbody pressure distributions. Data were also obtained with an dual sting support system and dummy wingtip booms to evaluate the interference introduced by the model wingtip support. This interference was on the order of twelve aircraft drag counts (Delta C sub D = 0.0012) at Mach number 1.2 and tended to decrease as the test Mach number was either increased or decreased. Changes in nozzle exit area for after-burning simulation produced significant local flow-field disturbances on the model aft end, but the increased pressure levels produced on the afterbody were compensated for by the decreased pressure levels on the nozzle so that the effect on the drag was less evident.

Book Wind tunnel Studies at Subsonic and Transonic Speeds of a Multiple mission Variable wing Sweep Airplane Configuration

Download or read book Wind tunnel Studies at Subsonic and Transonic Speeds of a Multiple mission Variable wing Sweep Airplane Configuration written by William J. Alford and published by . This book was released on 1959 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Report of the AGARD Ad Hoc Committee on Engine airplane Interference and Wall Corrections in Transonic Wind Tunnel Tests

Download or read book Report of the AGARD Ad Hoc Committee on Engine airplane Interference and Wall Corrections in Transonic Wind Tunnel Tests written by Organisation du Traité de l'Atlantique Nord. Committee on engine-airplane interference and wall corrections in transonic wind tunnel tests and published by . This book was released on 1971 with total page 145 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Application of Wind Tunnel Free Flight Technique for Wake Vortex Encounters

Download or read book Application of Wind Tunnel Free Flight Technique for Wake Vortex Encounters written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-08 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel investigation was conducted in the Langley 30- by 60-Foot Tunnel to assess the free-flight test technique as a tool in research on wake vortex encounters. A typical 17.5-percent scale business-class jet airplane model was flown behind a stationary wing mounted in the forward portion of the wind tunnel test section. The span ratio (model span-generating wingspan) was 0.75. The wing angle of attack could be adjusted to produce a vortex of desired strength. The test airplane model was successfully flown in the vortex and through the vortex for a range of vortex strengths. Data obtained included the model airplane body axis accelerations, angular rates, attitudes, and control positions as a function of vortex strength and relative position. Pilot comments and video records were also recorded during the vortex encounters. Brandon, Jay M. and Jordan, Frank L., Jr. and Stuever, Robert A. and Buttrill, Catherine W. Langley Research Center...