Effect of Cross-section Shape on the Aerodynamics Characteristics of Bodies at Mach Numbers from 2.50 to 4.63
Author: Dennis E. Fuller
Publisher:
Published: 1963
Total Pages: 40
ISBN-13:
DOWNLOAD EBOOKRead and Download eBook Full
Author: Dennis E. Fuller
Publisher:
Published: 1963
Total Pages: 40
ISBN-13:
DOWNLOAD EBOOKAuthor: Dennis E. Fuller
Publisher:
Published: 1963
Total Pages:
ISBN-13:
DOWNLOAD EBOOKAuthor: Dennis E. Fuller
Publisher:
Published: 1963
Total Pages: 0
ISBN-13:
DOWNLOAD EBOOKAuthor: Walter P. Nelms
Publisher:
Published: 1972
Total Pages: 68
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DOWNLOAD EBOOKAuthor: James F. Campbell
Publisher:
Published: 1967
Total Pages: 44
ISBN-13:
DOWNLOAD EBOOKAuthor: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-08-14
Total Pages: 32
ISBN-13: 9781725609662
DOWNLOAD EBOOKLongitudinal aerodynamic characteristics for a hydrogen-fueled hypersonic transport concept at Mach 6 are presented. The model components consist of four bodies with identical longitudinal area distributions but different cross-sectional shapes and widths, a wing, horizontal and vertical tails, and a set of wing-mounted nacelles simulated by slid bodies on the wing upper surface. Lift-drag ratios were found to be only sightly affected by fuselage planform width or cross sectional shape. Relative distribution of fuselage volume above and below the wing was found to have an effect on the lift-drag ratio, with a higher lift drag ratio produced by the higher wing position. Riebe, G. D. Langley Research Center NASA-TP-2235, L-15675, NAS 1.60:2235 RTOP 505-43-23-10...
Author: Robert A. Taylor
Publisher:
Published: 1959
Total Pages: 36
ISBN-13:
DOWNLOAD EBOOKAuthor: Gregory D. Riebe
Publisher:
Published: 1983
Total Pages: 36
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DOWNLOAD EBOOKAuthor: Leland Howard Jorgensen
Publisher:
Published: 1975
Total Pages: 88
ISBN-13:
DOWNLOAD EBOOKAn experimental investigation was conducted in the Ames 6- by 6-Foot Wind Tunnel to measure the static aerodynamic characteristics for two bodies of elliptic cross section and for their equivalent body of revolution. The equivalent body of revolution had the same length and axial distribution of cross-sectional area as the elliptic bodies. It consisted of a tangent ogive nose of fineness ratio 3 followed by a cylinder with a fineness ratio of 7. For the first body of elliptic cross section, the ratio of the semimajor axis to semiminor axis was held constant at 2 all along the body length. For the second elliptic body the nose was unchanged, but the aftersection was changed as follows: The cross-sectional axis ratio a/b was decreased from 2 to 1 over an axial distance of about 1.66 diam. Then, at this position, the a,b axis system was rotated 900, and the a/b ratio was increased back to 2 over the next 2.34 diam in length. Over the last length of three body diam, this rotated a/b ratio was held constant at 2.
Author: J. F. Reilly
Publisher:
Published: 1966
Total Pages: 78
ISBN-13:
DOWNLOAD EBOOKAn investigation was made at hypersonic Mach numbers to determine the effects of cross-section distribution on the static stability characteristics of bodies of revolution and to obtain the aerodynamic characteristics of these bodies. All of the bodies tested had the same length and all were circular in cross-section. The bodies tested were conic, bi-conic, and tri-conic. The tests were performed at Mach numbers of 5.35 and 6.71, and at unit Reynolds numbers from 1.5 x 100,000 to 3.2 x 100,000 per centimeter. The results indicate that under certain test conditions a body with a forecone followed by a frustum or frustum-flare combination exhibits, through the flow mechanism on the upper quarter of the body, an adverse center of pressure travel in the low angle of attack region (0 to 5 degrees). For a given moment reference point this yields both stable and unstable trim-points. (Author).