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Development Of A Supersonic Area Rule And An Application To The Design Of A Wing Body Combination Having High Lift To Drag Ratios
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Book Synopsis A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios by : Richard T. Whitcomb
Download or read book A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios written by Richard T. Whitcomb and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
Book Synopsis A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios by : Richard T. Whitcomb
Download or read book A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios written by Richard T. Whitcomb and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
Book Synopsis Transonic and Supersonic Wind-tunnel Tests of Wing-body Combinations Designed for High Efficiency at a Mach Number of 1.41 by : Frederick C. Grant
Download or read book Transonic and Supersonic Wind-tunnel Tests of Wing-body Combinations Designed for High Efficiency at a Mach Number of 1.41 written by Frederick C. Grant and published by . This book was released on 1960 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1966 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1960 with total page 418 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios by : Richard T. Whitcomb
Download or read book A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios written by Richard T. Whitcomb and published by . This book was released on 1960 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
Book Synopsis General Theory of Wave-drag Reduction for Combinations Employing Quasi-cylindrical Bodies with an Application to Swept-wing and Body Combinations by : Jack N. Nielsen
Download or read book General Theory of Wave-drag Reduction for Combinations Employing Quasi-cylindrical Bodies with an Application to Swept-wing and Body Combinations written by Jack N. Nielsen and published by . This book was released on 1955 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: The wing-body interference theory of NACA TN 2677 applied to symmetrical wings in combination with quasi-cylindrical bodies permits the direct calculation of pressure-distribution changes produced by body shape changes. This theory is used to determine the relative magnitued of the wave-drag reduction produced by changes in cylinder cross-sectional area and that produced changes in cross-sectional shape (without change in area). The body distortion is expressed as a Fourier series, and an integral equation is derived for the body shape for minimum drag for each Fourier component. Thus the wave-drag reductions for the various Fourier harmonics are independent and additive.
Book Synopsis Effect of Streamline Contouring in the Wing-fuselage Juncture in Combination with the Supersonic Area Rule on a Sweptback-wing-fuselage Configuration of High Fineness Ratio by : Charles D. Trescot
Download or read book Effect of Streamline Contouring in the Wing-fuselage Juncture in Combination with the Supersonic Area Rule on a Sweptback-wing-fuselage Configuration of High Fineness Ratio written by Charles D. Trescot and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Index to NASA Technical Publications by : United States. National Aeronautics and Space Administration
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Report written by and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Wave Drag of Arbitrary Configurations in Linearized Flow as Determined by Areas and Forces in Oblique Planes by : Harvard Lomax
Download or read book The Wave Drag of Arbitrary Configurations in Linearized Flow as Determined by Areas and Forces in Oblique Planes written by Harvard Lomax and published by . This book was released on 1955 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports for ... by :
Download or read book A Selected Listing of NASA Scientific and Technical Reports for ... written by and published by . This book was released on 1957 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Index of NASA Technical Publications by : United States. National Aeronautics and Space Administration
Download or read book Index of NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960 with total page 448 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of a Method of Designing the Sweptback-wing - Fuselage Juncture for Reducing the Drag at Transonic Speeds by : Robert R. Howell
Download or read book An Experimental Study of a Method of Designing the Sweptback-wing - Fuselage Juncture for Reducing the Drag at Transonic Speeds written by Robert R. Howell and published by . This book was released on 1955 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.84 and 1.32 at an angle of attack of zero degrees to determine the pressure-drag reductions attainable on a sweptback-wing - fuselage configuration tested consisted of a 45 degree sweptback wing of aspect ratio 4 in combination with a fineness-ratio-6.7 body. The results indicate that the pressure drag of a practical sweptback-wing - body configuration depends on the body cross-sectional shape as well as upon the longitudinal distribution of cross-sectional area.
Book Synopsis Index of NACA Technical Publications by : United States. National Advisory Committee for Aeronautics
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1959 with total page 382 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1960 with total page 416 pages. Available in PDF, EPUB and Kindle. Book excerpt:
