Serial/Series Title
4 Matching Results
Results open in a new window/tab.
Results:
1 - 4 of
4
A Wind-Tunnel Investigation of the Use of Spoilers for Obtaining Static Longitudinal Stability of a Canard-Missile Model in Reverse Flight
Report presenting an investigation in the stability tunnel of the use of spoilers for obtaining static longitudinal stability of a model of a canard missile in reverse flight. Results indicated that stable pitching-moment slopes can be obtained at angles of attack up to 11 degrees in the low speed range of the tests, but further investigation of high subsonic speeds will be necessary.
Date:
June 21, 1954
Creator:
Fletcher, Herman S.
System:
The UNT Digital Library
Effect of Nozzle Contour on Drag of Parabolic Afterbodies
Memorandum presenting an investigation of the effect of nozzle internal contour on afterbody drag in the 8- by 6-foot supersonic wind tunnel. Five different nozzle-afterbody configurations were evaluated. Results regarding the boattail pressure drag, base drag, and total drag are provided.
Date:
June 21, 1954
Creator:
Vargo, Donald J. & Englert, Gerald W.
System:
The UNT Digital Library
Effect of immersed surfaces in combustion zone on efficiency and stability of 5-inch diameter ram-jet combustor
Report presenting an extension of previous work on immersed surfaces in the combustion zone of a ramjet engine. The primary focus was to determine the effect of combustion efficiency and stability of blades located within the immediate wake of a V-gutter flame holder and to find some location and orientation of blades for optimum combustion efficiency and improved stability limits with a minimum of pressure loss.
Date:
June 21, 1954
Creator:
Reynolds, Thaine W. & Male, Donald W.
System:
The UNT Digital Library
Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbines for Turbojet Engines 2: Analytical Techniques
Memorandum presenting computation methods for analyzing turbojet-engine performance for a series of air-cooled nonafterburning and afterburning engines where all the engine components are simultaneously aerodynamically limited. The coolant-flow ratio was arbitrarily assigned so that the results of the analysis can be applied to any specific air-cooled blade configurations.
Date:
June 21, 1954
Creator:
Rossbach, Richard J.
System:
The UNT Digital Library