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Tuesday, May 5, 2020 | History

2 edition of Aerodynamic characteristics at Mach 6 of a wing-body concept for a hypersonic research airplane found in the catalog.

Aerodynamic characteristics at Mach 6 of a wing-body concept for a hypersonic research airplane

James L Dillon

Aerodynamic characteristics at Mach 6 of a wing-body concept for a hypersonic research airplane

by James L Dillon

  • 4 Want to read
  • 32 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Office, for sale by the National Technical Information Service in [Washington], Springfield, Va .
Written in English

    Subjects:
  • Hypersonic planes,
  • Stability of airplanes

  • Edition Notes

    StatementJames L. Dillon and Jimmy L. Pittman, Langley Research Center
    SeriesNASA technical paper ; 1249
    ContributionsPittman, Jimmy L., joint author, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Langley Research Center
    The Physical Object
    Pagination52 p. :
    Number of Pages52
    ID Numbers
    Open LibraryOL16807107M

    NM ~~ ilMIH NASA Technical Paper Experimental and Theoretical Aerodynamic Characteristics of Two Hypersonic Cruise Aircraft Concepts at Mach Numbers of , , and Jimmy L. Pittman and Gregory D. Riebe Larigley Research Center Hampton, Virginia r\l/N5A National Aeronautics and Space Administration Scientific and Technical. Get this from a library! Aerodynamic characteristics of a distinct wing-body configuration at Mach 6: experiment, theory, and the hypersonic isolation principle. [Jim A Penland; Jimmy L Pittman; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.].

    has better lift characteristics even at negative angles of attack and better stall characteristics. Angle of incidence. A stall is a condition in aerodynamics where the angle of attack increases beyond a certain point such that the lift begins to decrease. The angle at which this . Aerodynamic characteristics of a hypersonic research airplane concept having a 70 degree swept double delta wing at Mach numbers from to Jim A. Penland. Roger H. Fournier. Don C. Marcum, Jr. TN D Adaptation of the Theodorsen theory to the representation of an airfoil as a combination of a lifting line and a thickness Center: Langley Research Center.

    Get this from a library! Aerodynamic characteristics, including effect of body shape, of a Mach 6 aircraft concept. [Gregory D Riebe; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.]. The shape of the wing as viewed from directly above - deals with airflow in three dimensions, and is very important to understanding wing performance and airplane flight characteristics. Aspect ratio, taper ratio, and sweepback are factors in planform design that are very important to the overall aerodynamic characteristic of a wing.


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Aerodynamic characteristics at Mach 6 of a wing-body concept for a hypersonic research airplane by James L Dillon Download PDF EPUB FB2

AERODYNAMIC CHARACTERISTICS AT MACH 6 OF A HYPERSONIC RESEARCH AIRPLANE CONCEPT HAVING A 70° SWEPT DELTA WING Louis E. Clark and Christine B. Richie Langley Research Center SUMMARY An experimental investigation was conducted at Mach 6 to determine the hypersonic aerodynamic characteristics of an air-launched, delta-wing research aircraft concept.

Aerodynamic characteristics at Mach 6 of a wing-body concept for a hypersonic research airplane. [James L Dillon; Jimmy L Pittman; United States. National Aeronautics and Space Administration. The investigation consisted of configuration buildup from the basic body by adding a wing, center vertical tail, three-module scramjet, and six-module scramjet engine.

The test Mach number was six at a Reynolds number, based on model fuselage length, of ab, The investigation consisted of configuration buildup from the basic body by adding a wing, center vertical tail, three-module scramjet, and six-module scramjet engine.

The test Mach number was six at a Reynolds number, based on model fuselage length, of ab,Author: J. Pittman and J. Dillon. Aerodynamic characteristics at Mach 6 of a wing-body concept for a hypersonic research airplane / By James L.

Dillon, joint author. Jimmy L. Pittman, Langley Research Center. and United States. Report discussing an investigation to determine the aerodynamic characteristics of hypersonic missile configurations with cruciform trailing-edge flaps with all-movable control surfaces. The all-movable controls were found to produce much larger values of trim lift and normal acceleration than the trailing-edge-flap : Ross B.

Robinson, Peter T. Bernot. Aerodynamic Characteristics at Mach Numbers From to of a Wing-Body Design Concept for a Hypersonic Research Airplane James L. Dillon and Jimmy Pittman Langley Research Center Hampton, Virginia National Aeronautics and Space Administration Scientific and.

The static aerodynamic characteristics of a 1/30 scale model of a wing-body concept for a high speed research airplane were investigated in the Langley 20 inch Mach six tunnel. Investigation of the Aerodynamic Characteristics of a Hypersonic Transport Model at Mach number to 6, NASA TN D, (). Meteorologically induced variability of sonic-boom characteristics of supersonic aircraft in cruising flight.

Space Shuttle in NASA Langley Helium Tunnel at M = 20 (NASA SP) Hypersonic Aerodynamics. Introduction. Hypersonic vehicles are commonplace. There are many more of them than the supersonic aircraft discussed in the last chapter. Applications include missiles, launch vehicles and entry Size: 1MB.

Aerodynamic characteristics at Mach 6 of a hypersonic research airplane concept having a 70 ̊swept delta wing Author: Louis E Clark ; Christine B Richie ; United States. Aerodynamic Characteristics of a Hypersonic Research Airplane Concept Having a 70" Swept Double-Delta Wing at Mach Number Jim A.

Penland, Theodore R. Creel, Jr., and James L. Dillon Laqley Research Ceizter Ha mp to 12, Virginia NASA National Aeronautics and Space Administration Scientific and Technical Information Off ice Full text of "NASA Technical Reports Server (NTRS) Aerodynamic characteristics of a hypersonic research airplane concept having a 70 deg swept double-delta wing at Mach number " See other formats NASA Technical Paper NASA TP 12^2 c.1 loan copy: ret ur 2^5 AFWL TECHNICAL LII ^ KIRTLANO AFB* N.

Aerodynamic Characteristics of a Hypersonic Research Airplane Concept. Aerodynamic Characteristics of a model designed to represent an all-body, hypersonic cruise aircraft are presented for Mach numbers from to The configuration had a delta planform with an elliptic cone forebody and an afterbody.

Aerodynamics of delta wings with flaps at hypersonic speeds - Volume Issue - R. RameshCited by: 4. Aerodynamic Measurements of an Air-Breathing Hypersonic Vehicle at Mach to 8 Article in AIAA Journal 56(6) September with 60 Reads How we measure 'reads'. Fig. 6 Comparison of theory and experiment for configuration A, without vertical tails or engine, M=RL = •.

with the base pressure corrected to freest ream static pressure. The drag coefficients are referenced to the engine inlet tests on the lifting body (A) and the wing-body (B) Size: 2MB.

Start studying T-6 Aerodynamics. Learn vocabulary, terms, and more with flashcards, games, and other study tools. Welcome to the NASA's Guide to Hypersonics: Hypersonic aerodynamics is a special branch of the study of aeronautics.

The chief characteristic of hypersonic aerodynamics is that the temperature of the flow around the aircraft is so great that the chemistry of the gas must be considered.

At low hypersonic speeds, the molecular bonds vibrate, which changes the magnitude of the forces. Based on the concept of high-pressure capturing wings (HCW) [9], a family of hypersonic I-shaped aerodynamic configurations (HIAC) has been proposed by taking advantage of the favorable.

An experimental investigation of the low-speed longitudinal, lateral, and directional stability characteristics of a lifting-body hypersonic research airplane concept was con- ducted in a low-speed tunnel with a foot (meter) octagonal test section at the Langley Research Size: 2MB.The aerodynamic heating rate on axisymmetric cone-flare models under hypersonic conditions (Mach 6) is investigated by using infrared thermography.

The primary purpose of the work is to see the. Six-degree-of-freedom measurements have been performed with an aerodynamic model of a small-scale hypersonic air-breathing vehicle. The model was tested in two test campaigns in two different wind tunnels, with Mach numbers ranging from the supersonic to the hypersonic range (Mach to Mach Cited by: 2.