Comparison of Low-lift Drag at Mach Numbers from 0.74 to 1.37 of Rocket-boosted Models Having Externally Braced Wings and Cantilever Wings PDF Download
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Author: Waldo L. Dickens
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 22
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Book Description
An investigation has been conducted to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing the wing thickness while external braces were used to provide the necessary bending strength. The investigation consisted of flight training two rocket models having aspect ratio 3.04, unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data collected from the flight test of a model having a thicker cantilever wing of the same plan form were compared with data collected in this investigation.
Author: Waldo L. Dickens
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 22
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Book Description
An investigation has been conducted to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing the wing thickness while external braces were used to provide the necessary bending strength. The investigation consisted of flight training two rocket models having aspect ratio 3.04, unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data collected from the flight test of a model having a thicker cantilever wing of the same plan form were compared with data collected in this investigation.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
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Author: John D. Morrow
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 58
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Author: H. Herbert Jackson
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 32
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Author: Robert S. Osborne
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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Author: Edward C. Polhamus
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 28
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Author: Warren Jr Gillespie
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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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.
Author: Earl C. Jr Hastings
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Author: Warren Jr Gillespie
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
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