Author: Robert F. Peck
Publisher:
ISBN:
Category :
Languages : en
Pages : 33
Book Description
A Rocket-model Investigation of the Longitudinal Stability, Lift, and Drag Characteristics of the Douglas X-3 Configuration with Horizontal Tail of Aspect Ratio 4.33
Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Have a 60© Delta Wing and a High Unwept Horizontal Tail
Author: Robert F. Peck
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 32
Book Description
Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Having a 60 Degree Delta Wing and a High Unswept Horizontal Tail
Rocket-model Investigation of Lateral Stability Characteristics and Power Effects of a Jet-engine Airplane Configuration with Tail Boom at Mach Numbers from 1.15 to 1.37
Author: T. Bradley Curry
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 34
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 34
Book Description
Lift and Drag Characteristics of the Douglas X-3 Research Airplane Obtained During Demonstration Flights to a Mach Number of 1.20
Author: Donald R. Bellman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 23
Book Description
Lift and drag data were obtained during the manufacturer and Air Force demonstration flights of the Douglas X-3 airplane. The data covered the Mach number range from 0.82 to 1.20 with considerable variation in lift.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 23
Book Description
Lift and drag data were obtained during the manufacturer and Air Force demonstration flights of the Douglas X-3 airplane. The data covered the Mach number range from 0.82 to 1.20 with considerable variation in lift.
Stability of Two Rocket-propelled Models Having Aspect-ratio-5 Unswept Tails on a Long Body for the Mach Number Range of 1.7 to 2.4
Author: Reginald R. Lundstrom
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 48
Book Description
Two rocket models having cruciform, aspect-ratio-5, unwswept tails and a fineness-ratio-20 fuselage were flight tested over a Mach number range of approximately 1.7 to 2.4. One of the models had cruciform, aspect-ratio-3.4 forward surfaces in line with the tails. The models were given step disturbances by pulse rockets at intervals throughout the Mach number range and stability derivatives were obtained from the measured responses. The roll rates of the models varied from 10 radians per second to 5 radians per second.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 48
Book Description
Two rocket models having cruciform, aspect-ratio-5, unwswept tails and a fineness-ratio-20 fuselage were flight tested over a Mach number range of approximately 1.7 to 2.4. One of the models had cruciform, aspect-ratio-3.4 forward surfaces in line with the tails. The models were given step disturbances by pulse rockets at intervals throughout the Mach number range and stability derivatives were obtained from the measured responses. The roll rates of the models varied from 10 radians per second to 5 radians per second.
An Investigation of a 0.16-scale Model of the Douglas X-3 Airplane to Determine Means of Improving the Low-speed Longitudinal Stability and Control Characteristics
Flight Stability and Automatic Control
Author: Robert C. Nelson
Publisher: WCB/McGraw-Hill
ISBN: 9780071158381
Category : Aerodynamique / Aeronautique / Aerospatial / Automatique / Avion / Commande / Conception / Controle / Navigation / Stabilite
Languages : en
Pages : 441
Book Description
The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.
Publisher: WCB/McGraw-Hill
ISBN: 9780071158381
Category : Aerodynamique / Aeronautique / Aerospatial / Automatique / Avion / Commande / Conception / Controle / Navigation / Stabilite
Languages : en
Pages : 441
Book Description
The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.
Introduction to Aircraft Flight Mechanics
Author: Thomas R. Yechout
Publisher: AIAA
ISBN: 9781600860782
Category : Aerodynamics
Languages : en
Pages : 666
Book Description
Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
Publisher: AIAA
ISBN: 9781600860782
Category : Aerodynamics
Languages : en
Pages : 666
Book Description
Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
Static Longitudinal Stability of a Rocket Vehicle Having a Rear-facing Step Ahead of the Stabilizing Fins
Author: Robert J. Keynton
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 28
Book Description
"Tests were conducted at Mach numbers of 3.96 and 4.65 in the Langley Unitary Plan wind tunnel to determine the static longitudinal stability characteristics of a fin-stabilized rocket-vehicle configuration which had a rearward facing step located upstream of the fins. Two fin sizes and planforms, a delta and a clipped delta, were tested. The angle of attack was varied from 6° to -6° and the Reynolds number based on model length was about 10 x 106. The configuration with the larger fins (clipped delta) had a center of pressure slightly rearward of and an initial normal-force-curve slope slightly higher than that of the configuration with the smaller fins (delta) as would be expected. Calculations of the stability parameters gave a slightly lower initial slope of the normal-force curve than measured data, probably because of boundary-layer separation ahead of the step. The calculated center of pressure agreed well with the measured data. Measured and calculated increments in the initial slope of the normal-force curve and in the center of pressure, due to changing fins, were in excellent agreement indicating that separated flow downstream of the step did not influence flow over the fins. This result was consistent with data from schlieren photographs."--P. 1.
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 28
Book Description
"Tests were conducted at Mach numbers of 3.96 and 4.65 in the Langley Unitary Plan wind tunnel to determine the static longitudinal stability characteristics of a fin-stabilized rocket-vehicle configuration which had a rearward facing step located upstream of the fins. Two fin sizes and planforms, a delta and a clipped delta, were tested. The angle of attack was varied from 6° to -6° and the Reynolds number based on model length was about 10 x 106. The configuration with the larger fins (clipped delta) had a center of pressure slightly rearward of and an initial normal-force-curve slope slightly higher than that of the configuration with the smaller fins (delta) as would be expected. Calculations of the stability parameters gave a slightly lower initial slope of the normal-force curve than measured data, probably because of boundary-layer separation ahead of the step. The calculated center of pressure agreed well with the measured data. Measured and calculated increments in the initial slope of the normal-force curve and in the center of pressure, due to changing fins, were in excellent agreement indicating that separated flow downstream of the step did not influence flow over the fins. This result was consistent with data from schlieren photographs."--P. 1.