Author: John P. Mugler
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 79
Book Description
Pressure distributions on a thin conical cambered low-aspect-ratio delta wing have been obtained in the Langley 8-foot transonic tunnel over a Mach number range from 0.60 to 1.12 and at a Mach number of 1.43. Data were obtained for the wing in combination with a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2. The angle-of-attack range was from -4 to 20 degrees in most instances.
Pressure Measurements at Transonic and Low Supersonic Speeds on a Thin Conical Cambered Low-aspect-ratio Delta Wing in Combination with Basic and Indented Bodies
Author: John P. Mugler
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 79
Book Description
Pressure distributions on a thin conical cambered low-aspect-ratio delta wing have been obtained in the Langley 8-foot transonic tunnel over a Mach number range from 0.60 to 1.12 and at a Mach number of 1.43. Data were obtained for the wing in combination with a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2. The angle-of-attack range was from -4 to 20 degrees in most instances.
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 79
Book Description
Pressure distributions on a thin conical cambered low-aspect-ratio delta wing have been obtained in the Langley 8-foot transonic tunnel over a Mach number range from 0.60 to 1.12 and at a Mach number of 1.43. Data were obtained for the wing in combination with a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2. The angle-of-attack range was from -4 to 20 degrees in most instances.
Pressure Measurements Obtained in Flight at Transonic Speeds for a Conically Cambered Delta Wing
Author: Earl R. Keener
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 80
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 80
Book Description
Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2
Author: Marlowe D. Cassetti
Publisher:
ISBN:
Category : Transonic wind tunnels
Languages : en
Pages : 104
Book Description
An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Publisher:
ISBN:
Category : Transonic wind tunnels
Languages : en
Pages : 104
Book Description
An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Professional Measurements Obtained in Flight at Transonic Speeds for a Conically Cambered Delta Wing
Author: Earl R. Keener
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
Book Description
NASA Technical Note
Author:
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ISBN:
Category :
Languages : en
Pages : 442
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 442
Book Description
Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 860
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 860
Book Description
Index of NASA Technical Publications
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 494
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 494
Book Description
Index of NASA Technical Publications
Author: United States. National Aeronautics and Space Administration
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ISBN:
Category : Aeronautics
Languages : en
Pages : 448
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
Book Description
Index to NASA Technical Publications
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 296
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 296
Book Description