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The Design of Variable Mach Number Asymmetric Super-Sonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines

Description: "Two theoretical procedures are developed for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One procedure is applicable at Mach numbers less than approximately 3. This approach yields, without iteration, a nozzle for which the calculated exit flow is uniform at two Mach numbers and, with proper design, is nearly uniform at Mach numbers between, slightly above, and slightly below these two" (p. 1).
Date: April 11, 1951
Creator: Syvertson, Clarence A. & Savin, Raymond C.
Partner: UNT Libraries Government Documents Department

The Design of Variable Mach Number Asymmetric Supersonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines

Description: Report presenting two theoretical procedures for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One is for Mach numbers less than approximately 3 and one is for Mach numbers greater than 3.
Date: March 1953
Creator: Syvertson, Clarence A. & Savin, Raymond C.
Partner: UNT Libraries Government Documents Department

Effects of Boundary-Layer Separation on Normal Force and Center of Pressure of a Cone-Cylinder Model With a Large Base Flare at Mach Numbers From 3.00 to 6.28

Description: Report presenting testing of a body with a 22.5 degree conical nose, a 4-diameter-long cylindrical midsection, and a 20 degree cone-frustum tail flare. The tests were made over a variety of angles of attack and Mach numbers. Results regarding spark shadowgraph pictures and predictions versus the actual values were provided.
Date: October 3, 1955
Creator: Dennis, David H. & Syvertson, Clarence A.
Partner: UNT Libraries Government Documents Department

Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18

Description: Memorandum presenting a study of aerodynamic performance and static stability and control at hypersonic speeds. In the first part of the study, the effect of interference lift is investigated by tests of asymmetric models with conical fuselages and arrow plan-form wings. In the second part, the aerodynamic performance and static stability and control characteristics of a hypersonic glider are investigated in somewhat greater detail.
Date: September 17, 1958
Creator: Syvertson, Clarence A.; Gloria, Hermilio R. & Sarabia, Michael F.
Partner: UNT Libraries Government Documents Department

Inviscid Flow About Airfoils at High Supersonic Speeds

Description: Report presenting an investigation of steady flow about curved airfoils at high supersonic speeds. Testing demonstrated that within the limitation of the assumption of ideal gas flow, the shock-expansion method may be used with good accuracy to predict pressure distributions on curved airfoils at arbitrarily high Mach numbers.
Date: March 1952
Creator: Eggers, A. J., Jr. & Syvertson, Clarence A.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of a Body Flare for Obtaining Pitch Stability and a Body Flap for Obtaining Pitch Control in Hypersonic Flight

Description: Memorandum presenting the effectiveness of a body flare as a pitch-stabilizing device and a body flap as a pitch-control device investigated experimentally at Mach numbers from 3.00 to 6.25. The basic test body was rotationally symmetric and consisted of a fineness ratio 3 nose followed by a fineness ratio 9 afterbody. Results regarding the stability of the flared body, effect of body flap on lift and drag, trim conditions, flow visualization studies, and comparison of theory and experiment are provided.
Date: January 18, 1955
Creator: Eggers, A. J., Jr. & Syvertson, Clarence A.
Partner: UNT Libraries Government Documents Department

Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds

Description: Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuselage fineness ratio, effect of fuselage profile shape, and static longitudinal stability characteristics are provided.
Date: February 19, 1957
Creator: Syvertson, Clarence A.; Wong, Thomas J. & Gloria, Hermilo R.
Partner: UNT Libraries Government Documents Department

An Experimental Investigation of the Zero-Lift-Drag Characteristics of Symmetrical Blunt-Trailing-Edge Airfoils at Mach Numbers From 2.7 to 5.0

Description: Report presenting an investigation of the zero-lift-drag characteristics of nine symmetrical airfoils at a range of Mach and Reynolds numbers. Results regarding pressure and force data are also provided.
Date: April 29, 1953
Creator: Syvertson, Clarence A. & Gloria, Hermilo R.
Partner: UNT Libraries Government Documents Department