Aerodynamics Of A Sphere And An Oblate Spheroid For Mach Numbers From 0 6 To 10 5 Including Some Effects Of Test Conditions

DOWNLOAD

Download Aerodynamics Of A Sphere And An Oblate Spheroid For Mach Numbers From 0 6 To 10 5 Including Some Effects Of Test Conditions PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Aerodynamics Of A Sphere And An Oblate Spheroid For Mach Numbers From 0 6 To 10 5 Including Some Effects Of Test Conditions book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages. If the content not found or just blank you must refresh this page

Aerodynamics Of A Sphere And An Oblate Spheroid For Mach Numbers From 0 6 To 10 5 Including Some Effects Of Test Conditions

DOWNLOAD
Author : M. Leroy Spearman
language : en
Publisher:
Release Date : 1993

Aerodynamics Of A Sphere And An Oblate Spheroid For Mach Numbers From 0 6 To 10 5 Including Some Effects Of Test Conditions written by M. Leroy Spearman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1993 with Aerodynamics categories.

Aerodynamics Of A Sphere And An Oblate Spheroid For Mach Numbers From 0 6 To 10 5 Including Some Effects Of Test Conditions

DOWNLOAD
Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-08-20

Aerodynamics Of A Sphere And An Oblate Spheroid For Mach Numbers From 0 6 To 10 5 Including Some Effects Of Test Conditions written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-08-20 with categories.

Wind-tunnel tests were made for spheres of various sizes over a range of Mach numbers and Reynolds numbers. The results indicated some conditions where the drag was affected by changes in the afterbody pressure due to a shock reflection from the tunnel wall. This effect disappeared when the Mach number was increased for a given sphere size or when the sphere size was decreased for a given Mach number. Drag measurements and Schlieren photographs are presented that show the possibility of obtaining inaccurate data when tests are made with a sphere too large for the test section size and Mach number. Tests were also made of an oblate spheroid. The results indicated a region at high Mach numbers where inherent positive static stability might occur with the oblate-face forward. The drag results are compared with those for a sphere as well as those for various other shapes. The drag results for the oblate spheroid and the sphere are also compared with some calculated results. Spearman, M. Leroy and Braswell, Dorothy O. Langley Research Center RTOP 505-69-20-01...

Aerodynamics Of A Sphere And An Oblate Spheroid For Mach Numbers From 0 6 To 10 5 Including Some Effects Of Test Conditions

DOWNLOAD
Author : National Aeronautics and Space Administration NASA
language : en
Publisher:
Release Date : 2018-10-23

Aerodynamics Of A Sphere And An Oblate Spheroid For Mach Numbers From 0 6 To 10 5 Including Some Effects Of Test Conditions written by National Aeronautics and Space Administration NASA and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-10-23 with categories.

Wind-tunnel tests were made for spheres of various sizes over a range of Mach numbers and Reynolds numbers. The results indicated some conditions where the drag was affected by changes in the afterbody pressure due to a shock reflection from the tunnel wall. This effect disappeared when the Mach number was increased for a given sphere size or when the sphere size was decreased for a given Mach number. Drag measurements and Schlieren photographs are presented that show the possibility of obtaining inaccurate data when tests are made with a sphere too large for the test section size and Mach number. Tests were also made of an oblate spheroid. The results indicated a region at high Mach numbers where inherent positive static stability might occur with the oblate-face forward. The drag results are compared with those for a sphere as well as those for various other shapes. The drag results for the oblate spheroid and the sphere are also compared with some calculated results. Spearman, M. Leroy and Braswell, Dorothy O. Langley Research Center RTOP 505-69-20-01...

Government Reports Announcements Index

DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1994

Government Reports Announcements Index written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1994 with Science categories.

Government Reports Annual Index

DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1994

Government Reports Annual Index written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1994 with Government publications categories.

Aerodynamic Characteristics Of An Oblate Spheroid And A Sphere At Mach Numbers From 1 70 To 10 49

DOWNLOAD
Author : Lloyd S. Jernell
language : en
Publisher:
Release Date : 1970

Aerodynamic Characteristics Of An Oblate Spheroid And A Sphere At Mach Numbers From 1 70 To 10 49 written by Lloyd S. Jernell and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1970 with Aerodynamic load categories.

Drag coefficients of oblate spheroid and sphere at Mach numbers from 1.70 to 10.49.

Measurements Of The Static Pressure Distributions And Shock Shape On An Oblate Spheroid At Mach Numbers Of 3 And 6

DOWNLOAD
Author : Lionel Pasiuk
language : en
Publisher:
Release Date : 1966

Measurements Of The Static Pressure Distributions And Shock Shape On An Oblate Spheroid At Mach Numbers Of 3 And 6 written by Lionel Pasiuk and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with Mach number categories.

The results of experimental measurements of the static pressure distribution and bow shock shape on an oblate sphereoid are presented. This experiment was conducted at nominal Mach numbers of 3 and 6 and a free stream Reynolds number range of 2.3 X 106 to 5.8 X 106 per foot. Comparisons are made with the calculated values of several different laboratories.

Aerodynamic Characteristics Of An Oblate Spheroid And A Sphere At Mach Numbers From 1 70 To 10 49

DOWNLOAD
Author : Lloyd S. Jernell
language : en
Publisher:
Release Date : 1970

Aerodynamic Characteristics Of An Oblate Spheroid And A Sphere At Mach Numbers From 1 70 To 10 49 written by Lloyd S. Jernell and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1970 with Drag coefficients categories.

Handbook Of Inviscid Sphere Cone Flow Fields And Pressure Distributions

DOWNLOAD
Author : Alfred Merle Morrison
language : en
Publisher:
Release Date : 1975

Handbook Of Inviscid Sphere Cone Flow Fields And Pressure Distributions written by Alfred Merle Morrison and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Aerodynamic load categories.

This report contains numerical tables of aerodynamic coefficients and surface pressure distributions for sphere cone configurations as a function of angle of attack and Mach number. These results were generated by an NSWC/WOL computer code based on a finite difference solution of the steady inviscide three-dimensional compressible flow equation for a perfect gas [upsilon]= 1.4. Cone half angles of 50, 60, 80, 90, 100, 150 and 200 are considered. Truncated values are obtained at axial stations to a length of 200 times the sphere radius, over a Mach number range of 3.5, 5, 10, 20, 25 and 30, for an angle-of-attack span of 10, 30, 50, and 100. Center-of-pressure location, and axial- and normal-force coefficients are tabularly presented at each axial-length increment station. Surface pressure distributions are also presented at each axial-length increment station, including seven meridian plane angles over the half plane from windward to leeward ray. The techniques utilized in generating the tables are described, and comparisons between computed values and values measured in some wind-tunnel experiments are presented. The presentation format is discussed to establish the mechanics necessary to use the tables. The tables are divided into two volumes; the first containing pressure information, and the second, aerodynamic information.

Aerodynamic Interaction Effects Ahead Of A Sonic Jet Exhausting Perpendicularly From A Flat Plate Into A Mach Number 6 Free Stream

DOWNLOAD
Author : David J. Romeo
language : en
Publisher:
Release Date : 1961

Aerodynamic Interaction Effects Ahead Of A Sonic Jet Exhausting Perpendicularly From A Flat Plate Into A Mach Number 6 Free Stream written by David J. Romeo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with categories.

An investigation of the effects of the interaction ahead of a two-dimensional sonic jet exhausting perpendicularly into a Mach number 6 free stream from a flat-plate model has been conducted. The tests were made at an angle of attack of 0 degrees at a Reynolds number per foot of approximately 6 x 10(exp 6) and with conditions of both transitional and turbulent separation on the flat plate. The ratio of jet stagnation pressure to free-stream static pressure was varied from 8 to 460 and the jet slot width was varied from 0.001 to 0.05 inch. The force ratio (ratio of the normal force due to aerodynamic effect to the normal force due to reaction of jet), calculated ahead of the jet, was sizable and varied from 0.5 to 9. In general, the ratio increased with increasing pressure ratio and decreasing slot width. For the turbulent boundary-layer separation tests it was found that the first peak pressure and the chordwise pressure distribution of the separated boundary layer ahead of the jet were similar to those for a separation caused by a forward-facing step at the same test conditions.