Aerodynamic Characteristics Of An All Body Hypersonic Aircraft Configuration At Mach Numbers From 0 65 To 10 6

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Aerodynamic Characteristics of an All-body Hypersonic Aircraft Configuration at Mach Numbers from 0.65 to 10.6

Walter P. Nelms,Charles L. Thomas
Aerodynamic Characteristics of an All body Hypersonic Aircraft Configuration at Mach Numbers from 0 65 to 10 6 Book PDF

Author : Walter P. Nelms,Charles L. Thomas
Publisher : Unknown
Page : 108 pages
File Size : 47,7 Mb
Release : 1971
Category : Aerodynamics, Hypersonic
ISBN : UIUC:30112106692616

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Aerodynamic Characteristics of an All-body Hypersonic Aircraft Configuration at Mach Numbers from 0.65 to 10.6 by Walter P. Nelms,Charles L. Thomas Pdf

Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft are presented for Mach numbers from 0.65 to 10.6. The configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section. Detailed effects of varying angle of attack (-2 to 15 deg), angle of sideslip (-2 to 8 deg), Mach number, and configuration buildup were considered. In addition, the effectiveness of horizontal tail, vertical tail, and canard stabilizing and control surfaces was investigated. The results indicate that all configurations were longitudinally stable near maximum lift drag ratio. The configurations with vertical tails were directionally stable at all angles of attack. Trim penalties were small at hypersonic speeds for a center of gravity location representative of the airplane, but because of the large rearward travel of the aerodynamic center, trim penalties were severe at transonic Mach numbers.

Scientific and Technical Aerospace Reports

Anonim
Scientific and Technical Aerospace Reports Book PDF

Author : Anonim
Publisher : Unknown
Page : 1008 pages
File Size : 40,8 Mb
Release : 1978
Category : Aeronautics
ISBN : UIUC:30112075601028

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Scientific and Technical Aerospace Reports by Anonim Pdf

Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Index to NASA Technical Publications

United States. National Aeronautics and Space Administration
Index to NASA Technical Publications Book PDF

Author : United States. National Aeronautics and Space Administration
Publisher : Unknown
Page : 128 pages
File Size : 42,6 Mb
Release : 1960-07
Category : Electronic
ISBN : STANFORD:36105024165701

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Index to NASA Technical Publications by United States. National Aeronautics and Space Administration Pdf

Technical Abstract Bulletin

Anonim
Technical Abstract Bulletin Book PDF

Author : Anonim
Publisher : Unknown
Page : 684 pages
File Size : 40,7 Mb
Release : 2024-07-01
Category : Science
ISBN : CORNELL:31924057175469

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Technical Abstract Bulletin by Anonim Pdf

Supersonic Aerodynamic Characteristics of a Low-Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1.86 and a Body of Fineness Ratio 20

Anonim
Supersonic Aerodynamic Characteristics of a Low Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1 86 and a Body of Fineness Ratio 20 Book PDF

Author : Anonim
Publisher : Unknown
Page : 80 pages
File Size : 49,9 Mb
Release : 1960
Category : Aerodynamics, Supersonic
ISBN : NASA:31769000457039

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Supersonic Aerodynamic Characteristics of a Low-Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1.86 and a Body of Fineness Ratio 20 by Anonim Pdf

A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.

Aerodynamic Characteristics of a Hypersonic Transport Configuration at Mach 6.86

William John Small,Frank S. Kirkham,David E. Fetterman
Aerodynamic Characteristics of a Hypersonic Transport Configuration at Mach 6 86 Book PDF

Author : William John Small,Frank S. Kirkham,David E. Fetterman
Publisher : Unknown
Page : 36 pages
File Size : 42,5 Mb
Release : 1970
Category : Aerodynamics
ISBN : UIUC:30112106880054

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Aerodynamic Characteristics of a Hypersonic Transport Configuration at Mach 6.86 by William John Small,Frank S. Kirkham,David E. Fetterman Pdf

Research and Technology Program Digest

United States. National Aeronautics and Space Administration
Research and Technology Program Digest Book PDF

Author : United States. National Aeronautics and Space Administration
Publisher : Unknown
Page : 792 pages
File Size : 53,6 Mb
Release : 2024-07-01
Category : Electronic
ISBN : STANFORD:36105112109157

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Research and Technology Program Digest by United States. National Aeronautics and Space Administration Pdf

NASA Technical Note

Anonim
NASA Technical Note Book PDF

Author : Anonim
Publisher : Unknown
Page : 960 pages
File Size : 44,7 Mb
Release : 1972
Category : Aeronautics
ISBN : UOM:39015006100773

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NASA Technical Note by Anonim Pdf

Aerodynamic Characteristics at Mach Numbers from 0.33 to 1.20 of Wing-body Design Concept for a Hypersonic Research Airplane

James L. Dillon,Jimmy L. Pittman
Aerodynamic Characteristics at Mach Numbers from 0 33 to 1 20 of Wing body Design Concept for a Hypersonic Research Airplane Book PDF

Author : James L. Dillon,Jimmy L. Pittman
Publisher : Unknown
Page : 82 pages
File Size : 52,8 Mb
Release : 1977
Category : Aerodynamics, Hypersonic
ISBN : UIUC:30112105149030

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Aerodynamic Characteristics at Mach Numbers from 0.33 to 1.20 of Wing-body Design Concept for a Hypersonic Research Airplane by James L. Dillon,Jimmy L. Pittman Pdf

Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in Air

William I. Scallion
Aerodynamic Characteristics and Control Effectiveness of the HL 20 Lifting Body Configuration at Mach 10 in Air Book PDF

Author : William I. Scallion
Publisher : Unknown
Page : 62 pages
File Size : 49,8 Mb
Release : 1999
Category : Airplanes
ISBN : NASA:31769000633209

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Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in Air by William I. Scallion Pdf

A 0.0196-scale model of the HL-20 lifting body, one of several configurations proposed for future crewed spacecraft, was tested in the Langley 31-Inch Mach 10 Tunnel. The purpose of the tests was to determine the effectiveness of fin-mounted elevons, a lower surface flush-mounted body flap, and a flush-mounted yaw controller at hypersonic speeds. The nominal angle-of-attack range, representative of hypersonic entry, was 20 to 41 degrees, the sideslip angles were 0, 2, and -2 degrees, and the test Reynolds number was 1.06 x 10[factor 6] based on model reference length. The aerodynamic, longitudinal, and lateral control effectiveness along with surface oil flow visualizations are presented and discussed. The configuration was longitudinally and laterally stable at the nominal center of gravity. The primary longitudinal control, the fin-mounted elevons, could not trim the model to the desired entry angle of attack of 30 degrees. The lower surface body flaps were effective for roll control and the associated adverse yawing moment was eliminated by skewing the body flap hinge lines. A yaw controller, flush-mounted on the lower surface, was also effective, and the associated small rolling moment was favorable.