Sting Support Interference On Longitudinal Aerodynamic Characteristics Of Cargo Type Airplane Models At Mach 0 70 To 0 84
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Sting Support Interference On Longitudinal Aerodynamic Characteristics Of Cargo Type Airplane Models At Mach 0 70 To 0 84
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Author : Donald L. Loving
language : en
Publisher:
Release Date : 1967
Sting Support Interference On Longitudinal Aerodynamic Characteristics Of Cargo Type Airplane Models At Mach 0 70 To 0 84 written by Donald L. Loving and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with Airplanes categories.
Sting Support Interference On Longitudinal Aerodynamic Characteristics Of Cargo Type Airplane Models At Mach 0 70 To 0 84
DOWNLOAD
Author : Donald L. Loving
language : en
Publisher:
Release Date : 1967
Sting Support Interference On Longitudinal Aerodynamic Characteristics Of Cargo Type Airplane Models At Mach 0 70 To 0 84 written by Donald L. Loving and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with categories.
Longitudinal Stability And Control Characteristics At High Subsonic Speeds Of Two Models Of A Transonic Research Airplane With Wings And Horizontal Tails Of Aspect Ratios 4 2 And 2
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Author : Arvo A. Luoma
language : en
Publisher:
Release Date : 1950
Longitudinal Stability And Control Characteristics At High Subsonic Speeds Of Two Models Of A Transonic Research Airplane With Wings And Horizontal Tails Of Aspect Ratios 4 2 And 2 written by Arvo A. Luoma and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with Airplanes categories.
An investigation was made in the Langley 8-foot high-speed tunnel of two transonic research airplane models for Mach numbers up to approximately 0.95. The test Reynolds number at the highest speed was 1,600,000 for one model and 2,300,000 for the other model. The models were 1/16-schale and were supported in the tunnel on a sting. The wing and horizontal tail of one model were both of aspect ratio 4.2; the wing and horizontal tail of the other model were both of aspect ratio 2. The same fuselage and vertical tail were used on both models. The sweep of the 50-percent-chord line of the wings was zero degrees; the sweep of the 75-percent-chord line of the horizontal tails was zero degrees. Both wings had NACA 65-110 airfoil sections and both horizontal tails had NACA 65-008 airfoil sections. Lift drag, and pitching moment were determined by means of a strain-gage balance within the fuselage. Tare measurements were made to eliminate the interference effect of the sting.
Subsonic Sting Interference On The Aerodynamic Characteristics Of A Family Of Slanted Base Ogive Cylinders
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Author : Colin P. Britcher
language : en
Publisher:
Release Date : 1990
Subsonic Sting Interference On The Aerodynamic Characteristics Of A Family Of Slanted Base Ogive Cylinders written by Colin P. Britcher and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1990 with Aerodynamics categories.
Hosmer S Interest And Discount Table
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Author :
language : en
Publisher:
Release Date : 1839*
Hosmer S Interest And Discount Table written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1839* with Interest categories.
Interference On A Model Afterbody From Downstream Support Hardware At Transonic Mach Numbers
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Author : Earl A. Price (Jr.)
language : en
Publisher:
Release Date : 1981
Interference On A Model Afterbody From Downstream Support Hardware At Transonic Mach Numbers written by Earl A. Price (Jr.) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Aerodynamics, Transonic categories.
An experimental program was conducted to parametrically study the interference on an afterbody model that would be produced by the aft-support blade used with a wingtip support system. Geometric variables included the blade axial location, thickness, span, chord, and leading- and trailing-edge contours. Data were obtained over the Mach number range from 0.6 to 1.2 with the model at zero angle of attack. Interference was evaluated by comparing afterbody drag from a reference configuration, which had the aft-support blade removed, to the various configurations with a blade installed. A reasonable correlation of the blade interference effects on the afterbody drag coefficient was obtained, which included the influence of support blade axial position and blockage. Decreasing blade leading-edge bluntness by a factor of two resulted in a significant reduction of interference in the Mach number range from 0.9 to 1.1. Significantly greater interference was measured without jet flow than with jet flow. It is shown that a Euler equation computer code is a useful tool for the design of minimum interference support systems. (Author).
An Investigation At Mach Numbers 1 94 And 2 41 Of Jet Effects Upon The Longitudinal And Directional Stability Of A General Aircraft Configuration Employing Wing Tip Mounted Nacelles
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Author : Frank L. Clark
language : en
Publisher:
Release Date : 1958
An Investigation At Mach Numbers 1 94 And 2 41 Of Jet Effects Upon The Longitudinal And Directional Stability Of A General Aircraft Configuration Employing Wing Tip Mounted Nacelles written by Frank L. Clark and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with Airplanes categories.
Interference Effects Of Canard Controls On The Longitudinal Aerodynamic Characteristics Of A Winged Body At Mach 10
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Author : Cuyler W. Brooks
language : en
Publisher:
Release Date : 1968
Interference Effects Of Canard Controls On The Longitudinal Aerodynamic Characteristics Of A Winged Body At Mach 10 written by Cuyler W. Brooks and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with categories.
Static Lateral Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configuration
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Author : Kenneth W. Goodson
language : en
Publisher:
Release Date : 1961
Static Lateral Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configuration written by Kenneth W. Goodson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Stability of airplanes, Lateral categories.
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The aspect-ratio-3.50 wing had a taper of 0.067 and an unswept 0.80 chord line. The complete model was tested with a wing-chord-plane tail, a T-tail, and a biplane tail (combined T-tail and wing-chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 over a range of angle of attack of about ±20° and a range of sideslip of -15° to 13°. Some data were obtained with the horizontal stabilizer deflected. A few tests were also made with the wing tips clipped to an aspect ratio of 3.00.
Experimental Investigation At Low Speed Of Effects Of Fuselage Cross Section On Static Longitudinal And Lateral Stability Characteristics Of Models Having 0 And 45 Degrees Sweptback Surfaces
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Author : William Letko
language : en
Publisher:
Release Date : 1955
Experimental Investigation At Low Speed Of Effects Of Fuselage Cross Section On Static Longitudinal And Lateral Stability Characteristics Of Models Having 0 And 45 Degrees Sweptback Surfaces written by William Letko and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with Airplanes categories.
An experimental investigation at low speed was made to determine the effects of fuselage cross section on the static longitudinal and lateral stability characteristics of midwing airplane models having 0 and 45 degrees sweptback surfaces. The results indicate that the main effecs of fuselage cross section on the longitudinal and directional stability characteristics of the models at low angles of attack are caused by the direct contributions of the fuselage. At the high angles of attack, in additon to the direct contributions of the fuselage, wing-fuselage interference (sidewash) wit hthe tail decreases the tail contributions to the directional stability. The configuration consisting of the wing and deep fuselage produced the most detrimental effect, and the configuration consisting of the wing and shallow fuselage was the least detrimental in this respect. For the complete configurations tested, fuselage cross section had little effect on the range of linearity of the curves of yawing moment against sideslip angle for the angles of attack and sideslip investigated. In general, the configuration with the deep fuselage had the poorest directional characteristics of the models investigated.