Serial/Series Title
5 Matching Results
Results open in a new window/tab.
Results:
1 - 5 of
5
Influence of Automatic Control of Roll Coupling and Pitch-Up on Tail Loads
Memorandum presenting a study of the effects of automatic augmentation or controlling systems on the tail loads experienced in rolling maneuvers and in pitch-up. The results were calculated on an analog computer and the equations of five degrees of freedom were used for the rolling maneuvers and three degrees of freedom for pitch-up.
Date:
June 17, 1957
Creator:
Stone, Ralph W., Jr.
System:
The UNT Digital Library
Aerodynamics of Oscillating Control Surfaces at Transonic Speeds
Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.
Date:
June 17, 1957
Creator:
Thompson, Robert F. & Clevenson, Sherman A.
System:
The UNT Digital Library
Aerodynamic Heating and Boundary-Layer Transition on a 1/10-Power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-Stream Reynolds Numbers Up To 16 x 10(Exp 6)
Report presenting testing of a modified 1/10-power nose shape in free flight at Mach numbers up to 6.7. Measured heating rates were presented and compared with calculated values. Results regarding transition and comparison with previous investigations are provided.
Date:
June 17, 1957
Creator:
Garland, Benjamine J.; Swanson, Andrew G. & Speegle, Katherine C.
System:
The UNT Digital Library
Heat Transfer Measured on a Flat-Face Cylinder in Free Flight at Mach Numbers Up to 13.9
Report presenting an investigation of a five-stage rocket model at mach number 13.9 and an altitude of 81,500 feet. Temperatures were measured at 12 stations on the flat-face copper nose. Heating rates calculated from temperature time histories are compared to theoretical predictions of the rates.
Date:
June 17, 1957
Creator:
Stoney, William E., Jr. & Swanson, Andrew G.
System:
The UNT Digital Library
Investigation of an afterburning ramjet using gaseous hydrogen as fuel at Mach number of 3.0
Report presenting an investigation in the 10- by 10-foot supersonic wind tunnel on a 16-inch ramjet equipped with an afterburner and using gaseous hydrogen for the primary and afterburner fuels. The primary nozzle had a contraction ratio of 0.6 and the exit nozzle had a contraction ratio of 0.9. The results indicated that at a constant diffuser-exit Mach number, afterburner operation produces more than twice the thrust available without afterburning.
Date:
June 17, 1957
Creator:
Wasserbauer, Joseph F.
System:
The UNT Digital Library