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3 edition of Investigation of a supersonic cruise fighter model flow field found in the catalog.

Investigation of a supersonic cruise fighter model flow field

Investigation of a supersonic cruise fighter model flow field

  • 177 Want to read
  • 31 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in [Washington, D.C.], [Springfield, Va .
Written in English

    Subjects:
  • Aerodynamics, Transonic.

  • Edition Notes

    StatementDavid E. Reubush and E. Ann Bare.
    SeriesNASA technical memorandum -- 86361.
    ContributionsBare, E. Ann., United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17672750M

    Prof. Debasis Chakraborty has worked for 35 years in VSSC/ISRO and DRDL/DRDO on many practical aerodynamics and propulsion design problems pertaining to ISRO’s satellite launch vehicles and DRDO’s strategic and tactical missiles. For subsonic cruise the lift coefficient required was , and for supersonic cruise, which was considered to be the design point, the lift coefficient required was The lift curve slope of the wing was calculated to be per radian (/°) for the subsonic case, and per radian (/°) for supersonic cruise.

    WING CONFIGURATION EFFECTS ON FLOW FIELD AND AERODYNAMIC PERFORMANCE OF SUPERSONIC BIPLANE FOR SONIC-BOOM REDUCTION. Naoshi Kuratani*, Masahito Yonezawa*, Hiroshi Yamashita*, Shuichi Ozaki*, lower wing of supersonic biplane model. PSP is a coating-type molecular sensor that consists of luminescent molecules and polymer binder.   Free Flight Model Investigation of a Vertical Attitude VTOL Fighter. Hovering Light Tests of a Transport Vertical Take-Off Airplane. Free-Flight Tests of a Supersonic Transport Model with Thrust Vectoring for Roll Control. s F Thrust Vectoring. Flow Studies on a 49 Degree Swept Wing Model with Trailing Edge. HL in 30x

    A fighter designed for supersonic flight and high maneuverability has a thrust-to-weight ratio and wing loading that produce a fair amount of inherent short airfield capability. That capability can be improved with the addition of rough-field landing gear (for operating on . Supersonic is of utility almost exclusively for military purposes. The fighter aircraft uses supersonic to go into and out of a fight with another airplane or evade a missile. This done with afterburner on turbofan engines. Afterburners use tremen.


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Investigation of a supersonic cruise fighter model flow field Download PDF EPUB FB2

Base suitable for theory verification, a flow field investigation was conducted on a wind tunnel model of a supersonic cruise fighter. The investigation took place in the Langley Foot Transonic Tunnel at Mach numbers of, andand at angles of attack of 0°, 5°, and i0° (° maximum at M = ).

Flow field data for. Get this from a library. Investigation of a supersonic cruise fighter model flow field. [David E Reubush; E Ann Bare; United States. National Aeronautics and Space Administration.

Scientific and Technical Information Division.]. An investigation was conducted in the Langley Foot Transonic Tunnel to survey the flow field around a model of a supersonic cruise fighter configuration. Local values of angle of attack, side flow, Mach number, and total pressure ratio were measured with a single multi-holed probe in three survey areas on a model previously used for nacelle Author: D.

Reubush and E. Bare. A NASA Langley investigation was conducted in the foot Transonic Tunnel to survey the flow field around a model of a Supersonic cruise fighter configuration. In this investigation, a model of a. Investigation of a supersonic cruise fighter model flow field / By David E.

Reubush, E. Ann. Bare and Langley Research Center. Abstract. Prepared at Langley Research Center."November "es bibliographical references (p. 8).Mode of access: Internet. Measurement of aerodynamic forces. Air velocity and pressures are measured in several ways in wind tunnels.

Air velocity through the test section is determined by Bernoulli's ement of the dynamic pressure, the static pressure, and (for compressible flow only) the temperature rise in the airflow.

The direction of airflow around a model can be determined by tufts of yarn attached. A Theoretical Investigation of Supersonic jets in Subsonic Flow Fields by c. Young by the fan efflux of a high bypass ratio engine at cruise Mach number, A method of calculating the pressure distribution on the gas generator would be stant in the entire flow field.

Two-dimensional flow. Magnetohydrodynamic (MHD) power generation with supersonic non-equilibrium plasma is demonstrated. Capacitively coupled radio frequency (RF) discharge (6 MHz, maximum continual power output of W) was adopted to ionize the Mach number ( m/s), kg/m 3 airflow.

In a MHD channel of 16 mm × 10 mm × 20 mm, MHD open voltage of 10 V is realized in the magnetic field of. The first turbojet fighter developed by Mikoyan-Gurevich OKB was the Mikoyan-Gurevich MiG-9, which appeared in the years immediately after World War used a pair of reverse-engineered German BMW engines.

The MiG-9 was a troublesome design that suffered from weak, unreliable engines and control problems. Categorized as a first-generation jet fighter, it was designed with the straight.

At supersonic flight Mach numbers the adiabatic compression of the flow by the shock waves in the inlet system results in an increase in temperature at the entrance to the compressor section (station 2) while leaving the stagnation enthalpy unchanged from its free stream value.

Assuming, for the moment, that the ratio of specific heats remains constant permits us to calculate the stagnation. Experimental investigation of flame-holding capability of hydrogen transverse jet in supersonic cross-flow Symposium (International) on Combustion, Vol.

27, No. 2 Control of Flame-Holding in Supersonic Airflow by Secondary Air Injection. Get this from a library. Theoretical and experimental flow fields for a supersonic cruise fighter forebody.

[Steven F Yaros; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.]. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA A supersonic aircraft is an aircraft able to fly faster than the speed of sound (Mach number 1).

Supersonic aircraft were developed in the second half of the twentieth century and have been used almost entirely for research and military purposes. Only two, Tupolev Tu (first flight - Decem ) and the Concorde (first flight - March 2, ), ever entered service for civil use as.

Supersonic Aerodynamics Introduction There have actually only been a few truly supersonic airplanes. This means airplanes that can cruise supersonically.

Before the F, classic “supersonic” fighters used brute force (afterburners) and had extremely limited duration. As an example, consider the two defined supersonic missions for the. For NAL, it was a first-time-experience to undertake drop test of stores from a SuMKI aircraft model.

At their m low-speed wind tunnel, using Froude Scaling principles, the scientists. The Investigation also revealed the occurrence of an unusual I flow phenomenon at the leading- edge of the supersonic airfoils at the * higher Mach numbers.

This phenomenon, through the elimination- of an eztensive separated-flow condition over the forward part of the airfoil, effected a rather sudden increase in normal-force, coeffi. An array of subsonic counter-flow jets is studied as an active thermal protection system (TPS) for wing leading edges of hypersonic vehicles.

The performance is numerically estimated in the model case of a circular cylinder on the basis of the 2D compressible Navier-Stokes equations. In contrast to a single subsonic jet, an array of jets is robust against variation of the angle of attack; high.

Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = or to ). Usually the supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic speeds.

This complicates both computations and wind tunnel testing. Adeli R., Longo J.M.A., Emunds H. () Flow Field Study of a Supersonic Jet Exiting into a Supersonic Stream.

In: Rath HJ., Holze C., Heinemann HJ., Henke R., Hönlinger H. (eds) New Results in Numerical and Experimental Fluid Mechanics V. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol. 11 *Hill, G. C.; and *Waters, M. H.: Conceptual Design of airplanes operated at sustained supersonic cruise speeds.

The a Lift Fan Plus Lift/Cruise Fighter Aircraft. AIAA Aircraft Mach B transport powered by GE4 turbojet engines Design, Flight Test and Operations Meeting, 6th, Los was the only non-military, sustained supersonic cruise.

High-Speed Wind Tunnel Investigation of the Longitudinal Stability and Control Characteristics of a 1/Scale Model of the D Research Airplane at High Subsonic Mach Numbers and at a Mach Number of Characteristics of Nine .Aerospace (ISSN ) is a peer-reviewed open access journal of aeronautics and astronautics published monthly online by MDPI.

The European Aeronautics Science Network (EASN), and the ECATS International Association are affiliated with Aerospace and their members receive a discount on the article processing charges. Open Access —free for readers, with article processing charges (APC.