Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Download A Wind Tunnel Investigation Of Forces On Cones At Low Mach Numbers full books in PDF, epub, and Kindle. Read online A Wind Tunnel Investigation Of Forces On Cones At Low Mach Numbers ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author : David Litwack (CAPT, USAF.)
Publisher :
ISBN 13 :
Total Pages : 57 pages
Book Rating : 4.:/5 (132 download)
Download or read book A Wind-tunnel Investigation of Forces on Cones at Low Mach Numbers written by David Litwack (CAPT, USAF.) and published by . This book was released on 1965 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : David Litwack
Publisher :
ISBN 13 :
Total Pages : 68 pages
Book Rating : 4.:/5 (227 download)
Download or read book A Wind-tunnel Investigation of Forces on Cones at Low Mach Numbers written by David Litwack and published by . This book was released on 1965 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The investigation was conducted to obtain subsonic aerodynamic forces on cones. Nine aluminum cones varying in apex angel from 10 degrees to 90 degrees were tested. Lift, drag and pitching moment were measured at angles of attack varying from -5 deg. to 180 deg. in 10 degree increments and at a dynamic pressure of up to 200 lb./sq. ft. The measured data was first corrected for tare and interference effects; three-dimensional wind-tunnel-boundary-corrections were then applied to correct the data to free-air conditions. This data is presented in graphical form as lift, drag and pitching moment coefficient versus angle of attack for each cone. A plot of drag coefficient versus Reynolds Number at each angle of attack for the 30 degree cone and the 60 degree cone showed the drag almost constant for each angle of attack over the small range of Reynolds Numbers tested (Re = 15,000 to Re = 57,000). The maximum lift to drag ratio for the three smallest cones (10 deg. to 30 deg. cone apex angle) occurred at an angle of attack between 30 deg. to 40 deg.; for every other cone (40 deg. to 90 deg. cone apex angle) the maximum L/D was at an angle of attack between 120 deg. and 130 deg. (Author).
Author :
Publisher :
ISBN 13 :
Total Pages : 34 pages
Book Rating : 4.:/5 (317 download)
Download or read book Wind-tunnel Investigation at Mach Numbers from 1.47 to 4.62 of Static Aerodynamic Characteristics of Twelve Nose Cones Designed for Supersonic Impact written by and published by . This book was released on 1961 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : C. J. Schueler
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.:/5 (463 download)
Download or read book An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1.5 to 19.5 written by C. J. Schueler and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the test section flow blockage characteristics was conducted in the 12- by 12 inch supersonic wind tunnel (Tunnel E-1) of the Von Karman Gas Dynamics Facility (AEDC). The purpose of the tests was to determine whether a method of predicting the maximum size model which will permit the establishment of supersonic flow, based on the model frontal area and bow shock-wave strength, is applicable over a wide range of Mach numbers. The tests conducted over the Mach number range from 1.5 to 5 using test models consisting of 15, 20, and 20 degrees half-angle cones, cone-cylinder combinations, and a series of discs. The inadequacy of the one dimensional, normal shock theory for predicting allowable model sizes was reconfirmed in these tests. Furthermore a correlation based on shock wave strength and model frontal area was found to be suitable only over a limited range of Mach numbers. Permissible hemisphere-cylinder model sizes from several wind tunnels covering the Mach number range from 1.5 to 19.5 are also presented.
Author : William R. Wehrend
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (31 download)
Download or read book Wind-tunnel Investigation of the Static and Dynamic Stability Characteristics of a 10 Degree Semivertex Angle Blunted Cone written by William R. Wehrend and published by . This book was released on 1962 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 704 pages
Book Rating : 4.:/5 (31 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.:/5 (317 download)
Download or read book An Investigation at Mach Numbers from 1.47 to 2.87 of Static Stability Characteristics of Nine Nose Cones Designed for Supersonic Impact Velocities written by and published by . This book was released on 1959 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Maurice A. Sylvester
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.3/5 (91 download)
Download or read book Wind Tunnel Tests of the Redstone "B" Nose Cone at Mach Numbers from 1.75 to 5.00 written by Maurice A. Sylvester and published by . This book was released on 1963 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : PHILCO NEWPORT BEACH CALIF AERONUTRONIC DIV.
Publisher :
ISBN 13 :
Total Pages : 1 pages
Book Rating : 4.:/5 (227 download)
Download or read book Experimental Investigation of the Aerodynamic Characteristics of 9 Deg Half-angle Cones with Varying Degrees of Bluntness at Mach Number 9 written by PHILCO NEWPORT BEACH CALIF AERONUTRONIC DIV. and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel test was conducted in a 21 in. hypersonic facility to obtain force and moment data on right circular cones of varying degrees of bluntness. Normal forces, axial forces, and pitching moments were measured over an angle of attack range of -10 to +15 degrees, at Mach numbers of 7.25 and 9.00, and a Reynolds number range of 0.037 to 0.150 x 10 to the 6th power/in. Three 9-degree half-angle cones with ratios of nose tip radius to base radius of 0.03, 0.187, and 0.30 were tested. The experimental data was compared with theoretical data, and the two were in good agreement. (Author).
Author : John P. Jr Mugler
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (317 download)
Download or read book Transonic Wind Tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Five Nose Cones Designed for Supersonic Impact written by John P. Jr Mugler and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Richard J. Re
Publisher :
ISBN 13 :
Total Pages : 292 pages
Book Rating : 4.:/5 (317 download)
Download or read book Wind Tunnel Investigation of Three Axisymmetric Cowls of Different Lengths at Mach Numbers from 0.60 to 0.92 written by Richard J. Re and published by . This book was released on 1993 with total page 292 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 106 pages
Book Rating : 4.:/5 (317 download)
Download or read book Wind Tunnel Investigation of the Aerodynamic Characteristics of Five Forebody Models at High Angles of Attack at Mach Numbers from 0.25 to 2 written by and published by . This book was released on 1975 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : B. J. Griffith
Publisher :
ISBN 13 :
Total Pages : 38 pages
Book Rating : 4.3/5 (91 download)
Download or read book Ablation and Viscous Effects on the Force and Moment Characteristics of Slender Cone Models at Mach 10 Under Laminar Flow Conditions written by B. J. Griffith and published by . This book was released on 1975 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive wind tunnel investigation was conducted at Mach number 10 on 4- and 5-deg half-angle cones in order to study ablation and viscous effects under laminar flow conditions. Attention was focused on (1) the mode of ablation simulation, (2) obtaining consistent pitch plane force measurements in the angle-of-attack range from 0 to 4 deg, (3) the effect of bluntness, and (4) viscous effects over as large a Reynolds number range as possible. The subliming ablator used was camphor, which is compared to blowing through a porous surface using (1) nitrogen, (2) argon, and (3) sulphur hexafluoride (SF6) gases.
Author :
Publisher :
ISBN 13 :
Total Pages : 430 pages
Book Rating : 4.:/5 (319 download)
Download or read book NASA Technical Note written by and published by . This book was released on 1963 with total page 430 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Stuart L. Treon
Publisher :
ISBN 13 :
Total Pages : 40 pages
Book Rating : 4.:/5 (31 download)
Download or read book Static Aerodynamic Characteristics of Short Blunt Cones with Various Nose and Base Cone Angles at Mach Numbers from 0.6 to 5.5 and Angles of Attack to 180 Degrees written by Stuart L. Treon and published by . This book was released on 1961 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : G. M. Gregorek
Publisher :
ISBN 13 :
Total Pages : 64 pages
Book Rating : 4.E/5 ( download)
Download or read book A Variable Atmosphere Hypersonic Wind Tunnel for Similitude Studies written by G. M. Gregorek and published by . This book was released on 1966 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William R. Wehrend
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (31 download)
Download or read book A Wind-tunnel Investigation of the Effect of Changes in Base Contour on the Damping in Pitch of a Blunted Cone written by William R. Wehrend and published by . This book was released on 1963 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
