Preliminary Base Pressures Obtained from the X-15 Airplane at Mach Numbers from 1.1 to 3.2 PDF Download

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Preliminary Base Pressures Obtained from the X-15 Airplane at Mach Numbers from 1.1 to 3.2

Preliminary Base Pressures Obtained from the X-15 Airplane at Mach Numbers from 1.1 to 3.2 PDF Author: Edwin J. Saltzman
Publisher:
ISBN:
Category :
Languages : en
Pages : 32

Book Description


Preliminary Base Pressures Obtained from the X-15 Airplane at Mach Numbers from 1.1 to 3.2

Preliminary Base Pressures Obtained from the X-15 Airplane at Mach Numbers from 1.1 to 3.2 PDF Author: Edwin J. Saltzman
Publisher:
ISBN:
Category :
Languages : en
Pages : 32

Book Description


Preliminary Base Pressures Obtained from the X-15 Airplane at Mach Numbers from 1.1 to 3.2

Preliminary Base Pressures Obtained from the X-15 Airplane at Mach Numbers from 1.1 to 3.2 PDF Author: Edwin J. Saltzman
Publisher:
ISBN:
Category :
Languages : en
Pages : 1

Book Description
Base pressure measurements were made on the fuselage, 10 degree-wedge vertical fin, and side fairing of the X-15 airplane. Data are presented for Mach numbers between 1.1 and 3.2 for both powered and unpowered flight. Comparisons are made with data from small-scale-model tests, semiempirical estimates, and theory. The results of this preliminary study show that operation of the interim rocket engines reduces the base drag of the X-15 by 25 to 35% throughout the test Mach number range. Values of base drag coefficient for the side fairing and fuselage obtained from X-15 wind-tunnel models were adequate for predicting the over-all full-scale performance of the test airplane. The leading-edge sweep of the upper movable vertical fin was not an important factor affecting the fin base pressure. The power-off base pressure coefficients of the upper movable vertical fin are in general agreement with the small-scale blunt-trailing-edge-wing data of several investigators and with two-dimensional t eory. (Author).

Base Pressure Coefficients Obtained from the X-15 Airplane for Mach Numbers Up to 6

Base Pressure Coefficients Obtained from the X-15 Airplane for Mach Numbers Up to 6 PDF Author: Edwin J. Saltzman
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 56

Book Description


Comparison of Wind-tunnel and Flight-measured Base Pressures from the Sharp-leading-edge Upper Vertical Fin of the X-15 Airplane for Turbulent Flow at Mach Numbers from 1.5 to 5.0

Comparison of Wind-tunnel and Flight-measured Base Pressures from the Sharp-leading-edge Upper Vertical Fin of the X-15 Airplane for Turbulent Flow at Mach Numbers from 1.5 to 5.0 PDF Author: Sheryll Goecke Powers
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 44

Book Description


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Category :
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