Data Report for a Test Program to Study Transonic Flow Fields About Wing-Body/Pylon/Store Combinations. Volume II. Flow Field Survey Data for Configurations 21 and 22
Data Report for a Test Program to Study Transonic Flow Fields About Wing-Body/Pylon/Store Combinations. Volume II. Flow Field Survey Data for Configurations 21 and 22

Author: S. S. Stahara

Publisher:

Published: 1978

Total Pages: 247

ISBN-13:

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This volume of the data report presents the flow-field survey data for configurations 21 and 22 at Mach numbers M1 = 0.925, M2 = 0.950, and M3 = 1.05 and angles of attack alpha = 0 deg, 2 deg, and 5 deg. The data were obtained in the 4T Wind Tunnel at Arnold Engineering and Development Center. The tests were performed at a nominal Reynolds number per foot of 3.0 million.

Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores. Volume II. Mach Number 0.925 Flow-Field Survey Data for the 4-Percent Thick Wing-Body Combination
Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores. Volume II. Mach Number 0.925 Flow-Field Survey Data for the 4-Percent Thick Wing-Body Combination

Author: Stanley C Perkins (Jr)

Publisher:

Published: 1977

Total Pages: 249

ISBN-13:

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A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume II, presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 0.925.

Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores. Volume V. Flow-Field Survey Data for the 6-Percent Thick Wing-Body Combination
Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores. Volume V. Flow-Field Survey Data for the 6-Percent Thick Wing-Body Combination

Author: Stanley C Perkins (Jr)

Publisher:

Published: 1977

Total Pages: 337

ISBN-13:

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A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Flow velocities and static pressures were also measured near the tunnel walls to provide outer flow field information. Volume V presents the tabulated flow-field data for 6-percent thick wing model.

Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores. Volume IV. Mach Number 1.025 Flow-Field Survey Data for the 4-Percent Thick Wing-Body Combination
Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores. Volume IV. Mach Number 1.025 Flow-Field Survey Data for the 4-Percent Thick Wing-Body Combination

Author: Stanley C Perkins (Jr)

Publisher:

Published: 1977

Total Pages: 248

ISBN-13:

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A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume IV presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 1.025.

Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores. Volume III. Mach Number 0.975 Flow-Field Survey Data for the 4-Percent Thick Wing-Body Combination
Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores. Volume III. Mach Number 0.975 Flow-Field Survey Data for the 4-Percent Thick Wing-Body Combination

Author: Stanley C Perkins (Jr)

Publisher:

Published: 1977

Total Pages: 249

ISBN-13:

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A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume III presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 0.975.

Aeronautical Engineering
Aeronautical Engineering

Author:

Publisher:

Published: 1993

Total Pages: 712

ISBN-13:

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A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)