Time Vector Determined Lateral Derivatives Of A Swept Wing Fighter Type Airplane With Three Different Vertical Tails At Mach Numbers Between 0 70 And 1 48
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Time Vector Determined Lateral Derivatives Of A Swept Wing Fighter Type Airplane With Three Different Vertical Tails At Mach Numbers Between 0 70 And 1 48
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Author : Chester H. Wolowicz
language : en
Publisher:
Release Date : 1956
Time Vector Determined Lateral Derivatives Of A Swept Wing Fighter Type Airplane With Three Different Vertical Tails At Mach Numbers Between 0 70 And 1 48 written by Chester H. Wolowicz and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Airplanes categories.
As part of the flight research program conducted on a swept-wing fighter-type airplane, rudder-pulse maneuvers were performed at altitudes from 30,000 to 43,000 feet over a Mach number range of 0.71 to 1.48 to determine the lateral stability characteristics relative to the stability axes, in general, and the lateral derivative characteristics, in particular. The time-vector method of analysis was used. Four configurations were employed in the investigation. Three configurations involved three different vertical tails with varying aspect ratio or area, or both. The fourth configuration employed a large tail, which had been used in the third configuration, and an extension of the wing tips.
Static Lateral Stability And Control Characteristics Of A Model Of A 45 Degree Swept Wing Fighter Airplane With Various Vertical Tails At Mach Numbers Of 1 41 1 61 And 2 01
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Author : M. Leroy Spearman
language : en
Publisher:
Release Date : 1956
Static Lateral Stability And Control Characteristics Of A Model Of A 45 Degree Swept Wing Fighter Airplane With Various Vertical Tails At Mach Numbers Of 1 41 1 61 And 2 01 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 1956 with categories.
Flight Determined Static Lateral Stability And Control Characteristics Of A Swept Wing Fighter Airplane To A Mach Number Of 1 39
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Author : Gene J. Matranga
language : en
Publisher:
Release Date : 1957
Flight Determined Static Lateral Stability And Control Characteristics Of A Swept Wing Fighter Airplane To A Mach Number Of 1 39 written by Gene J. Matranga and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Airplanes categories.
The static lateral stability characteristics of a swept-wing fighter-type airplane incorporating three vertical-tail configurations and two wing configurations were investigated at an altitude of 40,000 feet over a Mach number range from 0.72 to 1.39. The data obtained were determined during constant-heading sideslips and wings-level turns, aileron rolls, and abrupt rudder pulses.
Static Lateral Stability And Control Characteristics Of A Model Of A 45 Swept Wing Fighter Airplane With Various Vertical Tails At Mach Numbers Of 1 41 1 61 And 2 01
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Author : M. Leroy Spearman
language : en
Publisher:
Release Date : 1956
Static Lateral Stability And Control Characteristics Of A Model Of A 45 Swept Wing Fighter Airplane With Various Vertical Tails At Mach Numbers Of 1 41 1 61 And 2 01 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 1956 with Airplanes categories.
The Longitudinal And Lateral Aerodynamic Characteristics At Mach Numbers Of 1 41 And 2 20 Of A Variable Sweep Fighter Model With Wing Sweeps Varying From 25 Deg To 75 Deg
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Author :
language : en
Publisher:
Release Date : 1963
The Longitudinal And Lateral Aerodynamic Characteristics At Mach Numbers Of 1 41 And 2 20 Of A Variable Sweep Fighter Model With Wing Sweeps Varying From 25 Deg To 75 Deg written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1963 with categories.
A Comparison Of The Measured And Predicted Lateral Oscillatory Characteristics Of A 35 Deg Swept Wing Fighter Airplane
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Author :
language : en
Publisher:
Release Date : 1955
A Comparison Of The Measured And Predicted Lateral Oscillatory Characteristics Of A 35 Deg Swept Wing Fighter Airplane written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with categories.
Results of tests of a 35 deg swept-wing fighter airplane, during which lateral oscillations were performed over a Mach number range from 0.41 to 0.79 at a pressure altitude of 10,000 feet and from 0.49 to 1.04 at 35,000 feet, are presented in this report. Experimental and computed values for the period of the lateral oscillation and time required to damp to half amplitude are shown. One sample oscillation time history is included for each test altitude. The airplane was found to be laterally stable, statically and dynamically, throughout the range of speeds tested. At both altitudes, the variation with Mach number of the period of the lateral oscillation was satisfactorily predicted from available and estimated aerodynamic and mass parameters. The time required to damp to half amplitude, as measured from flight at both altitudes, varied with Mach number in essentially the same manner as predicted from computations. The measured damping was somewhat better than that obtained from computations for the altitude of 35,000 feet, particularly at a Mach number of 0.92. An increase in time to damp to half amplitude was noted between Mach numbers of 0.95 and 1.04.
The Time Vector Method For Lateral Stability Investigations
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Author : K. H. Doetsch
language : en
Publisher:
Release Date : 1967
The Time Vector Method For Lateral Stability Investigations written by K. H. Doetsch and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with Stability of airplanes, Lateral categories.
Lateral Stability Investigation At Mach Numbers From 0 8 To 1 7 Of Two Rocket Boosted Models Of An Airplane Configuration With A 45 Degree Swept Wing And A Low Horizontal Tail
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Author : John C. McFall
language : en
Publisher:
Release Date : 1957
Lateral Stability Investigation At Mach Numbers From 0 8 To 1 7 Of Two Rocket Boosted Models Of An Airplane Configuration With A 45 Degree Swept Wing And A Low Horizontal Tail written by John C. McFall and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Airplanes categories.
Rocket-boosted free-flight tests of two models of an airplane configuration having a 45 degree swept wing and a low horizontal-tail position have provided lateral stability derivatives and control effectiveness data for a Mach number range from 0.8 to 1.7. The experimental lateral stability derivatives presented are corrected to rigid conditions and compared with theoretically calculated rigid derivatives. The results are presented without detailed analysis.
Longitudinal And Lateral Aerodynamic Characteristics At Mach Numbers Of 1 61 And 2 20 Of A Variable Sweep Tactical Fighter Model With Wing Sweeps Of 65 Deg 85 Deg And 106 Deg
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Author :
language : en
Publisher:
Release Date : 1962
Longitudinal And Lateral Aerodynamic Characteristics At Mach Numbers Of 1 61 And 2 20 Of A Variable Sweep Tactical Fighter Model With Wing Sweeps Of 65 Deg 85 Deg And 106 Deg written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with categories.
Static Longitudinal And Lateral Aerodynamic Characteristics At Mach Numbers Of 2 36 And 2 86 Of A Variable Sweep Airplane Configuration Having Vertical Ramp Inlets
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Author :
language : en
Publisher:
Release Date : 1963
Static Longitudinal And Lateral Aerodynamic Characteristics At Mach Numbers Of 2 36 And 2 86 Of A Variable Sweep Airplane Configuration Having Vertical Ramp Inlets written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1963 with categories.