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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

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. The use of an inclined and curved sonic line is an essential feature of this approach, The second procedure requires iteration and is used far designs at Mach numbers exceeding 3. Although it is not a necessary feature, an inclined and curved sonic line is also used in this procedure. In both approaches the flow field dawn stream of the sonic line is determined using the method of characteristics.
Date: April 11, 1951
Creator: Syvertson, Clarence A. & Savin, Raymond C.
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

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

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