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Boundary-Layer Transition at High Reynolds Numbers as Obtained in Flight of a 20 Degree Cone-Cylinder With Wall to Local Stream Temperature Ratios Near 1.0

Description: Boundary-layer transition data at low ratios of wall to local stream temperature have been obtained during the free flight of a highly polished cone-cylinder to a maximum Mach number of 5.02 A maximum transition Reynolds number of 32 x 10(exp 6) occurred at a distance of 25.84 inches from the cone apex. The temperature ratio at transition for a local Mach number of 4.0 was approximately 1.30 as compared with theoretical infinite stability solutions of 1.47 and 1.65 by Dunn and Lin (three-dimens… more
Date: November 3, 1955
Creator: Rabb, Leonard & Disher, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of pentaborane fuel in 9.75-inch-diameter ram-jet engine with downstream fuel injection

Description: Report presenting a flight test of pentaborane fuel in an air-launched ramjet engine with a design free-stream Mach number of 1.8. The ramjet used in the investigation had a revised spray bar-flameholder configuration. Results regarding propulsive thrust and propulsive-thrust specific fuel consumption are provided.
Date: April 22, 1957
Creator: Disher, John H. & Jones, Merle L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of the cooling characteristics of a two-row radial engine installation 1: cooling correlation

Description: Report presenting flight tests to determine the cooling characteristics of a two-row radial engine at altitude in a twin-engine airplane and to investigate the accuracy with which low-altitude cooling-correlation equations can be used for making cooling predictions at higher altitudes. Satisfactory correlation of the cooling variables was obtained at both altitudes by the NACA-cooling method.
Date: July 1946
Creator: Bell, E. Barton; Morgan, James E.; Disher, John H. & Mercer, Jack R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of a 20-Inch-Diameter Steady-Flow Ram Jet

Description: Memorandum presenting a flight investigation conducted on a 20-inch-diameter steady-flow ramjet at a range of altitudes and free-stream Mach numbers. Results regarding the variation of combustion efficiency with fuel-air ratio and pressure altitude, effects of combustion-chamber-inlet velocity, and altitude on the operating range of fuel-air ratio are provided. The ramjet unit operated smoothly over the entire range of velocities and altitudes with the exception of occasional rough operation at… more
Date: January 14, 1948
Creator: Disher, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight investigation of 16-inch diameter supersonic ram-jet unit

Description: Report presenting an investigation of a series of 16-inch-diameter ramjet engine in free flight in order to determine the performance of ramjet units in flight at supersonic speeds and to study methods for improving the performance. Results regarding the telemeter data recorded by ground stations, static pressures, variation of altitude with time after release, variation of flight velocities, and fuel-air ratio are provided. Partial failure of the measuring equipment prevented a complete evalua… more
Date: May 28, 1948
Creator: Kinghorn, George F. & Disher, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Performance of 16-Inch-Diameter Supersonic Ram-Jet Units 3: Four Units Designed for Combustion-Chamber-Inlet Mach Number of 0.245 at Free-Stream Mach Number of 1.8 (Units D-1, D-2, D-3, and D-4)

Description: Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.
Date: June 28, 1950
Creator: Disher, John H. & Rabinowitz, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight performance of a rocket-boosted, air-launched 16-inch-diameter ram-jet engine at Mach numbers up to 2.20

Description: From Summary: "The investigation of air-launched ram-jet engines has been extended to include a study of models with a nominal design free-stream Mach number of 2.40. These models require auxiliary thrust in order to attain a flight speed at which the ram jet becomes self-accelerating. A rocket-boosting technique for providing this auxiliary thrust is described and time histories of two rocket-boosted ram-jet flights are presented. In one flight, the model attained a maximum Mach number of 2.20… more
Date: February 3, 1953
Creator: Disher, John H.; Kohl, Robert C. & Jones, Merle L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary drag and heat-transfer data obtained from air-launched cone-cylinder test vehicle over Mach number range from 1.5 to 5.18

Description: From Summary: "An air-launched cone-cylinder test vehicle designed to obtain data at Mach numbers above 4.0 was rocket boosted from a release Mach number of 5.18. The vehicle was launched at an altitude of 35,000 feet and reached peak velocity of 5150 feet per second at 28,500 feet. The total-drag coefficient (based on maximum cross-sectional area) decreased gradually from 0.31 at a Mach number of 1.75 to 0.145 at a Mach number of 5.18, while the Reynold's number (based on body length) increase… more
Date: November 16, 1953
Creator: Messing, Wesley E.; Rabb, Leonard & Disher, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Initial Performance Investigation of Pentaborane Fuel in Free-Flight Ram-Jet Engine

Description: Memorandum presenting an investigation with a ramjet utilizing pentaborane fuel in order to evaluate promising high-energy fuels under actual flight conditions. During descent, the engine accelerated to a Mach number of 1.45 when a flame-out believed due to spray-bar failure took place. Results regarding time history, pressure recovery, thrust, thrust-minus-drag, and drag coefficient, and comparison with hydrocarbon fuel are provided.
Date: January 24, 1957
Creator: Disher, John H. & Rabb, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Pentaborane Fuel in 9.75-Inch-Diameter Ram-Jet Engine at Low Equivalence Ratio

Description: Report presenting an investigation of the performance of pentaborane fuel at relatively low equivalence ratios using a 9.75-inch-diameter ramjet engine using pentaborane at an average equivalence ratio of approximately 0.23. Time histories of the flight conditions and combustion chamber conditions, total-temperature ratio, fuel flow, pressure recovery, thrust, propulsive thrust, and drag coefficients, and comparison with hydrocarbon fuel are provided.
Date: March 29, 1955
Creator: Jones, Merle L. & Disher, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Observation of Laminar Flow on a Blunted 15 Degree Cone-Cylinder in Free Flight at High Reynolds Numbers and Free-Stream Mach Numbers to 8.17

Description: "A highly polished 15 degree included-angle cone-cylinder with hemispherical tip has been flown to obtain boundary-layer transition and heat-transfer data. The model was launched from a carrier plane at an altitude of 47,500 feet. Laminar flow existed at a Reynolds number greater than 38.5 x 10(exp) 6 on the cylinder when the model was at the peak free-stream Mach number of 8.17. The results indicate an appreciable and favorable effect of tip bluntness in raising the allowable skin temperature … more
Date: October 15, 1956
Creator: Disher, John H. & Rabb, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Pentaborane Fuel in Rocket Boosted 9.75-Inch-Diameter Ramjet Engine With Convergent-Divergent Exhaust Nozzle

Description: Memorandum presenting a flight test of a pentaborane-fueled air-launched ramjet engine with convergent-divergent exhaust nozzle. The engine was boosted to a Mach number of about 2.00 by a small internally housed rocket; the ramjet then accelerated to a maximum free-stream Mach number of 3.02 at an altitude of 29,500 feet.
Date: September 17, 1957
Creator: Disher, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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