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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Testing of a photoelectric photometer. 2: Observational testing
The versatility is demonstrated of the 41 cm. Tortugas reflector's photoelectric system through observations of V566 Oph and R CrB with four associated AAVSO comparison stars. These observations were made between May and October, 1974.
An analysis of data related to the minimum temperatures for valid testing in cryogenic wind tunnels using nitrogen as the test gas
The minimum operating temperature which avoids adverse low temperature effects, such as condensation, has been determined at a free stream Mach number of 0.85 for flow over a 0.137 meter airfoil mounted at zero incidence in the Langley 1/3 meter transonic cryogenic tunnel. The onset of low temperature effects is established by comparing the pressure coefficient measured at a given orifice for a particular temperature with those measured at temperatures sufficiently above where low temperature effects might be expected to occur. The pressure distributions over the airfoil are presented in tabular form. In addition, the comparisons of the pressure coefficient as a function of total temperature are presented graphically for chord locations of 0, 25, 50, and 75 percent. Over the 1.2 to 4.5 atmosphere total pressure range investigated, low temperature effects are not detected until total temperatures are 2 K, or more, below free stream saturation temperatures.
Test plan for cold flow development test system
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Measurement and testing problems experienced during FAA's emissions testing of general aviation piston engines
The importance of measuring accurate air and fuel flows as well as the importance of obtaining accurate exhaust pollutant measurements were emphasized. Some of the problems and the corrective actions taken to incorporate fixes and/or modifications were identified.
Self streamlining wind tunnel: Low speed testing and transonic test section design
Comprehensive aerodynamic data on an airfoil section were obtained through a wide range of angles of attack, both stalled and unstalled. Data were gathered using a self streamlining wind tunnel and were compared to results obtained on the same section in a conventional wind tunnel. The reduction of wall interference through streamline was demonstrated.
Fisheries imaging radar surveillance test /FIRST/ - Bering Sea test
A joint NOAA, U.S. Coast Guard and NASA program is being conducted to determine if a synthetic aperture radar (SAR) system, such as planned for NASA's SEASAT, can be useful in monitoring fishing vessels within the newly established 200-mile fishing limit. As part of this program, data gathering field operations were conducted over concentrations of foreign fishing vessels in the Bering Sea off Alaska in April 1976. The Jet Propulsion Laboratory developed synthetic aperture L-band radar which was flown aboard the NASA Convair 990 aircraft, with a Coast Guard cutter and C-130 aircraft simultaneously gathering data to provide both radar imagery and sea truth information on the vessels being imaged. Results indicate that synthetic aperture radar systems have potential for all weather detection, enumeration and classification of fishing vessels.
Base pressure and heat transfer tests of 0.0225-scale space shuttle plume simulation model 19-OTS in the NASA-Lewis 10 x 10 foot SWT (test 1H34)
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Design, Manufacture, Development, Test, and Evaluation of Boron/Aluminum Structural Components for Space Shuttle. Volume 3: Shear Beam Component Test and Analysis
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USDA Application Test System (ATS) session: The application test system, an approach for technology transfer
There are no author-identified significant results in this report.
FUR 87 test report: Evaluation of RMS capability to deploy and berth the payload flight test article
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Results of heat transfer tests in the Arnold Engineering Development Center: von Karman facility tunnels A and B utilizing Space Shuttle orbiter thin skin thermocouple models 56-0, 60-0 and 83-0: Volume 1: Tests: OH-84B, OH-105, IH-102
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Results of heat transfer tests in the Arnold Engineering Development Center: von Karman facility tunnels A and B utilizing Space Shuttle orbiter thin skin thermocouple models 56-0, 60-0 and 83-0. Volume 2: Tests: OH-84B, OH-105, IH-102
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Results of heat transfer tests in the Arnold Engineering Development Center: von Karman facility tunnels A and B utilizing Space Shuttle orbiter thin skin thermocouple models 56-0, 60-0 and 83-0: Volume 3: Tests: OH-84B, OH-105, IH-102
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Results of heat transfer tests in the Arnold Engineering Development Center: von Karman facility tunnels A and B utilizing Space Shuttle orbiter thin skin thermocouple models 56-0, 60-0 and 83-0. Volume 4: Tests: OH-84B, OH-105, IH-102
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Test results from the NASA/Rockwell International Space Shuttle 0.0175-scale orbiter models 56-0/60-0 and 0.04-scale orbiter forebody model 83-0 conducted in the NASA/ARC 3.5 foot hypersonic wind tunnel, test OH110
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Control software for two dimensional airfoil tests using a self-streamlining flexible walled transonic test section
Operation of the Transonic Self-Streamlining Wind Tunnel (TSWT) involved on-line data acquisition with automatic wall adjustment. A tunnel run consisted of streamlining the walls from known starting contours in iterative steps and acquiring model data. Each run performs what is described as a streamlining cycle. The associated software is presented.
Nationwide forestry applications program. Renewable resources inventory project. Multiresource Inventory Methods Pilot test (phase 1). Evaluation of Multiresource Analysis and Information System (MAIS) processing components. Kershaw County, South Carolina feasibility test, volume 3
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