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Longitudinal Characteristics at Transonic and Supersonic Speeds of a Rocket-Propelled Airplane Model Having a 60-Degree Delta Wing and Low Swept Horizontal Tail
Report presenting measurements of the longitudinal stability, lift, and drag characteristics of an airplane configuration with a 60 degree delta wing and a swept horizontal tail mounted near the wing plane extended at a range of Mach numbers using the rocket-model technique. Comparisons are made to data form a similar model with the tail mounted above the wing plane.
Date:
September 15, 1955
Creator:
Peck, Robert F. & Coltrane, Lucille C.
System:
The UNT Digital Library
Transonic Wind-Tunnel Investigation of the Aerodynamic Loading Characteristics of a 60 Degree Delta Wing in the Presence of a Body With and Without Indentation
Report presenting an investigation in the transonic pressure tunnel to determine the aerodynamic loading characteristics of a 60 degree delta wing in the presence of a body with and without body indentation in accordance with the transonic-area-rule concept. Tests covered a range of angles of attack and Mach numbers. Results regarding force and moment coefficients and curves are provided.
Date:
September 15, 1955
Creator:
Mugler, John P., Jr.
System:
The UNT Digital Library
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 3 - Swept-Wing Fighter-Bomber Configuration With Large and Small Stores. Mach Number, 1.61
Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a fighter-bomber airplane with a large and a small external store.
Date:
September 15, 1955
Creator:
Smith, Norman F. & Carlson, Harry W.
System:
The UNT Digital Library
The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations 3: swept-wing fighter-bomber configuration with large and small stores. Mach number 1.61
Report presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61. Separate forces on a store, a swept wing, and a swept-wing-fuselage combination were measured. This report presents data on a configuration that simulated a fighter-bomber airplane with a large and a small external store.
Date:
September 15, 1955
Creator:
Smith, Norman F. & Carlson, Harry W.
System:
The UNT Digital Library
Note on Hovering Turns with Tandem Helicopters
"The source of an appreciable pitching-moment difference between left and right hovering turns for a tandem helicopter is described. The difference in pitching moment results from the difference in rotational speed of the counter rotating rotors with respect to the air while the helicopter is turning" (p. 1).
Date:
September 15, 1955
Creator:
Reeder, John P. & Tapscott, Robert J.
System:
The UNT Digital Library
An Evaluation of a Rolleron-Roll-Rate-Stabilization System for a Canard Missile Configuration at Mach Numbers From 0.9 to 2.3
Report presenting a linear stability analysis and flight-test investigation on a rolleron-roll-rate stabilization system for a canard missile. This type of damper provides roll damping by the action of gyro-actuated uncoupled wing-tip ailerons. A dynamic roll instability predicted by the analysis was confirmed by flight testing and was subsequently eliminated by introducing control-surface damping about the rolleron hinge line.
Date:
September 15, 1955
Creator:
Nason, Martin L.; Brown, Clarence A., Jr. & Rock, Rupert S.
System:
The UNT Digital Library