Author: Robert O. Piland
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
Book Description
The Zero-lift Drag of a 60 [degrees] Delta-wing-body Combination (AGARD Model 2) Obtained from Free-flight Tests Between Mach Numbers of 0.8 and 1.7
Author: Robert O. Piland
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
Book Description
The Zero-lift Drag of a 60 Degree Delta-wing-body Combination (AGARD Model 2) Obtained from Free-flight Tests Between Mach Numbers of 0.8 and 1.7
Author: Robert O. Piland
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 11
Book Description
The zero-lift drag of a 60 degree delta-wing-body combination (designated AGARD Model 2) has been determined by free-flight tests of two models between Mach numbers of 0.8 and 1.7. These Mach numbers correspond to Reynolds numbers, based on body length, of 4,000,000 and 12,000,000, respectively. An estimate of the drag of the configuration was made by summing the estimates of the drag of the various components. The agreement between measured and estimated drag is good.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 11
Book Description
The zero-lift drag of a 60 degree delta-wing-body combination (designated AGARD Model 2) has been determined by free-flight tests of two models between Mach numbers of 0.8 and 1.7. These Mach numbers correspond to Reynolds numbers, based on body length, of 4,000,000 and 12,000,000, respectively. An estimate of the drag of the configuration was made by summing the estimates of the drag of the various components. The agreement between measured and estimated drag is good.
The Journal of the Royal Aeronautical Society
Author: Royal Aeronautical Society
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 938
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 938
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 992
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 992
Book Description
Large-scale Flight Measurements of Zero-lift Drag and Low-lift Drag of 10 Wing-body Configurations at Mach Numbers from 0.8 to 1.6
Author: John D. Morrow
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 58
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 58
Book Description
A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0
Author: Robert S. Osborne
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
Book Description
International Aerospace Abstracts
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1052
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1052
Book Description
Results of Flight Tests to Determine the Zero-lift Drag Characteristics of a 60 Degree Delta Wing with NACA 65-006 Airfoil Section and Various Double-wedge Sections at Mach Numbers from 0.7 to 1.6
Author: Clement J. Welsh
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 15
Book Description
Results of an exploratory free-flight investigation at zero-lift of several rocket-powered drag research models equipped with 60 degree swept-back delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 15
Book Description
Results of an exploratory free-flight investigation at zero-lift of several rocket-powered drag research models equipped with 60 degree swept-back delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness.
Results of Flight Tests to Determine the Zero-lift Drag Characteristics of a 60 Degrees Delta Wing with NACA 65-006 Airfoil Section and Various Double-wedge Sections at Mach Numbers from 0.7 to 1.6
Author: Clement J. Welsh
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Results of a Flight Investigation to Determine the Zero-Lift Drag Characteristics of a 60 Deg Delta Wing with NACA 65-006 Airfoil Section and Various Double-Wedge Sections at Mach Numbers from 0.7-1.6
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models equipped with 60 deg sweptback delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness. The results of the investigation showed that, of the double-wedge sections with 6 percent thickness, the two sections with positions of maximum thickness at 20 and 50 percent of the chord had drag coefficients approximately equal through the transonic and supersonic Mach number range and had similarly occurring drag rises. The section with position of maximum thickness at 80 percent chord had a drag rise occurring at a Mach number M of approximately 0.15 lower than the drag rise of the other two sections. At M = 1.0, this section had drag coefficients more than twice as large as those of the other two sections; however, this difference decreased with increasing supersonic Mach numbers. The wing drag calculated by the linearized theory was in qualitative agreement with the test results in indicating the effects of varying the position of maximum thickness. The double-wedge section of 5 percent thickness with position of maximum thickness at 50 percent chord had fairly constant drag coefficients throughout the supersonic region, which ranged from about 50 to 80 percent of the drag coefficients for the similar section with twice the thickness ratio. The theoretical wing drag for this section was in very good agreement with the experimental value. The NACA 65-006 airfoil section had lower drag coefficients throughout the test region than any of the double-wedge sections of the same thickness ratio, although at the highest Mach numbers covered by these tests, the differences became very small.
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models equipped with 60 deg sweptback delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness. The results of the investigation showed that, of the double-wedge sections with 6 percent thickness, the two sections with positions of maximum thickness at 20 and 50 percent of the chord had drag coefficients approximately equal through the transonic and supersonic Mach number range and had similarly occurring drag rises. The section with position of maximum thickness at 80 percent chord had a drag rise occurring at a Mach number M of approximately 0.15 lower than the drag rise of the other two sections. At M = 1.0, this section had drag coefficients more than twice as large as those of the other two sections; however, this difference decreased with increasing supersonic Mach numbers. The wing drag calculated by the linearized theory was in qualitative agreement with the test results in indicating the effects of varying the position of maximum thickness. The double-wedge section of 5 percent thickness with position of maximum thickness at 50 percent chord had fairly constant drag coefficients throughout the supersonic region, which ranged from about 50 to 80 percent of the drag coefficients for the similar section with twice the thickness ratio. The theoretical wing drag for this section was in very good agreement with the experimental value. The NACA 65-006 airfoil section had lower drag coefficients throughout the test region than any of the double-wedge sections of the same thickness ratio, although at the highest Mach numbers covered by these tests, the differences became very small.