Isolated Performance At Mach Numbers From 0 60 To 2 86 Of Several Expendable Nozzle Concepts For Supersonic Applications
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Isolated Performance At Mach Numbers From 0 60 To 2 86 Of Several Expendable Nozzle Concepts For Supersonic Applications
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-06-15
Isolated Performance At Mach Numbers From 0 60 To 2 86 Of Several Expendable Nozzle Concepts For Supersonic Applications 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 2018-06-15 with categories.
Investigations have been conducted in the Langley 16-Foot Transonic Tunnel (at Mach numbers from 0.60 to 1.25) and in the Langley Unitary Plan Wind Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of 0 deg to determine the isolated performance of several expendable nozzle concepts for supersonic nonaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ratio, and cruciform shroud flap vectoring were investigated. The nozzle pressure ratio range, which was a function of Mach number, was between 1.9 and 11.8 in the 16-Foot Transonic Tunnel and between 7.9 and 54.9 in the Unitary Plan Wind Tunnel. Discharge coefficient, thrust-minus-drag, and the forces and moments generated by vectoring the divergent shroud flaps (for Mach numbers of 0.60 to 1.25 only) of a cruciform nozzle configuration were measured. The shortest nozzle had the best thrust-minus-drag performance at Mach numbers up to 0.95 but was approached in performance by other configurations at Mach numbers of 1.15 and 1.25. At Mach numbers above 1.25, the cruciform nozzle configuration having the same expansion ratio (2.64) as the fixed geometry nozzles had the best thrust-minus-drag performance. Ventilation of the fixed geometry divergent shrouds to the nozzle external boattail flow generally improved thrust-minus-drag performance at Mach numbers from 0.60 to 1.25, but decreased performance above a Mach number of 1.25. Re, Richard J. and Berrier, Bobby L. and Abeyounis, William K. Langley Research Center RTOP 706-17-21-05
Isolated Performance At Mach Numbers From 0 60 To 2 86 Of Several Expendable Nozzle Concepts For Supersonic Applications
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Author : Richard J. Re
language : en
Publisher:
Release Date : 2001
Isolated Performance At Mach Numbers From 0 60 To 2 86 Of Several Expendable Nozzle Concepts For Supersonic Applications written by Richard J. Re and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2001 with Mach number categories.
Investigations have been conducted in the Langley 16-Foot Transonic Tunnel (at Mach numbers from 0.60 to 1.25) and in the Langley Unitary Plan Winf Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of O° to determine the isolated performane of several expendable nozzle concepts for supersonic noaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ration, and cruciform shroud flap vectoring were investigated. The nozzle pressure ration range, which was a function of Mach number, was between 1.9 and 11.8 in the 16-Foot Transonic Tunnel and between 7.9 and 54.9 in the Unitary Plan WInd Tunnel. Discharge coefficient, thrust-minus-drag, and the forces and moments generated by vectoring the divergent shroud flaps (for Mach numbers of 0.60 to 1.25 only) of a cruciform nozzle configuration were measured.
Thrust Performance Of Isolated Plug Nozzles With Two Types Of 40 Spoke Noise Suppressor At Mach Numbers From 0 To 0 45
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Author : Douglas E. Harrington
language : en
Publisher:
Release Date : 1974
Thrust Performance Of Isolated Plug Nozzles With Two Types Of 40 Spoke Noise Suppressor At Mach Numbers From 0 To 0 45 written by Douglas E. Harrington and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with categories.
Performance Of An Isolated Two Dimensional Variable Geometry Wedge Nozzle With Translating Shroud And Collapsing Wedge At Speeds Up To Mach 2 01
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Author : Donald L. Maiden
language : en
Publisher:
Release Date : 1975
Performance Of An Isolated Two Dimensional Variable Geometry Wedge Nozzle With Translating Shroud And Collapsing Wedge At Speeds Up To Mach 2 01 written by Donald L. Maiden and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Aerodynamics, Supersonic categories.
A wind-tunnel investigation was conducted to determine the aeropropulsion performance (thrust-minus-drag) of a single-engine, variable-geometry, two-dimensional (2-D) wedge nozzle with simulated translating-shroud and collapsing-wedge mechanisms. The investigation was conducted statically and at Mach numbers from 0.60 to 2.01 at an angle of attack of 0 deg and at varied jet total-pressure ratios up to 21, depending on the Mach number. The results indicate that the isolated aeropropulsion performance of a variable-geometry two-dimensional wedge nozzle is competitive with axisymmetric nozzles at transonic and supersonic speeds, but the isolated performance is slightly inferior for static take-off and low subsonic speeds. With the use of a simple tertiary-air ejector, the static take-off performance was increased.
Thrust Performance Of Isolated Two Dimension Suppressed Plug Nozzles With And Without Ejectors At Mach Numbers From 0 To 0 45
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Author : Douglas E. Harrington
language : en
Publisher:
Release Date : 1976
Thrust Performance Of Isolated Two Dimension Suppressed Plug Nozzles With And Without Ejectors At Mach Numbers From 0 To 0 45 written by Douglas E. Harrington and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with Airplanes categories.
Thrust Performance Of Isolated Two Dimensional Suppressed Plug Nozzles With And Without Ejectors At Mach Numbers From 0 To 0 45
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Author : Douglas E. Harrington
language : en
Publisher:
Release Date : 1976
Thrust Performance Of Isolated Two Dimensional Suppressed Plug Nozzles With And Without Ejectors At Mach Numbers From 0 To 0 45 written by Douglas E. Harrington and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with categories.
Performance Of An Isolated Two Dimensional Wedge Nozzel With Fixed Cowl And Variable Wedge Centerbody At Mach Numbers Up To 2 01
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Author : Donald L. Maiden
language : en
Publisher:
Release Date : 1976
Performance Of An Isolated Two Dimensional Wedge Nozzel With Fixed Cowl And Variable Wedge Centerbody At Mach Numbers Up To 2 01 written by Donald L. Maiden and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with Rockets (Aeronautics) categories.
Thrust Performance Of Isolated 36 Chute Suppressor Plug Nozzles With And Without Ejectors At Mach Numbers From 0 To 0 45
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Author : Douglas E. Harrington
language : en
Publisher:
Release Date : 1975
Thrust Performance Of Isolated 36 Chute Suppressor Plug Nozzles With And Without Ejectors At Mach Numbers From 0 To 0 45 written by Douglas E. Harrington and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Airplanes categories.
Parametric Investigation Of Single Expansion Ramp Nozzles At Mach Numbers From 0 60 To 1 20
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-27
Parametric Investigation Of Single Expansion Ramp Nozzles At Mach Numbers From 0 60 To 1 20 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 2018-07-27 with categories.
An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the effects of varying six nozzle geometric parameters on the internal and aeropropulsive performance characteristics of single-expansion-ramp nozzles. This investigation was conducted at Mach numbers from 0.60 to 1.20, nozzle pressure ratios from 1.5 to 12, and angles of attack of 0 deg +/- 6 deg. Maximum aeropropulsive performance at a particular Mach number was highly dependent on the operating nozzle pressure ratio. For example, as the nozzle upper ramp length or angle increased, some nozzles had higher performance at a Mach number of 0.90 because of the nozzle design pressure was the same as the operating pressure ratio. Thus, selection of the various nozzle geometric parameters should be based on the mission requirements of the aircraft. A combination of large upper ramp and large lower flap boattail angles produced greater nozzle drag coefficients at Mach number greater than 0.80, primarily from shock-induced separation on the lower flap of the nozzle. A static conditions, the convergent nozzle had high and nearly constant values of resultant thrust ratio over the entire range of nozzle pressure ratios tested. However, these nozzles had much lower aeropropulsive performance than the convergent-divergent nozzle at Mach number greater than 0.60. Capone, Francis J. and Re, Richard J. and Bare, E. Ann Langley Research Center NASA-TP-3240, L-17067, NAS 1.60:3240 RTOP 505-62-30-01...
Computational Prediction Of Isolated Performance Of An Axisymmetric Nozzle At Mach Number 0 90
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Author : John R. Carlson
language : en
Publisher:
Release Date : 1994
Computational Prediction Of Isolated Performance Of An Axisymmetric Nozzle At Mach Number 0 90 written by John R. Carlson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1994 with Fluid dynamics categories.