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Preliminary Flight Measurements of the Total-Pressure Recovery of a Split-Wing Ram-Jet Inlet at Mach Numbers from 1.4 to 3.16

Description: From Summary: "Flight tests were made to determine the total-pressure recovery of a split-wing ram-jet inlet with a fixed area exit 20 percent larger than the inlet throat over a Mach number range from 1.4 to 3.16. Total-pressure-recovery measurements at the diffuser exist station indicated abrupt pressure changes in the total-pressure profile throughout the Mach number range. Comparisons of average total-pressure recovery with the theoretical total-pressure recovery showed good agreement."
Date: March 4, 1954
Creator: Hinners, Arthur H., Jr.
Partner: UNT Libraries Government Documents Department

Preliminary flight tests of the N.A.C.A. Roots type aircraft engine supercharger

Description: An investigation of the suitability of the N.A.C.A. Roots type aircraft engine supercharger to flight-operating conditions, as determined the effects of the use of the supercharger upon engine operation and airplane performance, is described in this report. Attention was concentrated on the operation of the engine-supercharger unit and on the improvement of climbing ability; some information concerning high speeds at altitude was obtained. The supercharger was found to be satisfactory under flight-operating conditions. Although two failures occurred during the tests, the causes of both were minor and have been eliminated. Careful examination of the engines revealed no detrimental effects which could be attributed to supercharging. Marked improvements in climbing ability and high speeds at altitude were effected. It was also found that the load which could be carried to a given moderate or high altitude in a fixed time was considerably augmented. A slight sacrifice of low-altitude performance was necessitated, however, by the use of a fixed-pitch propeller. From a consideration of the very satisfactory flight performance of the Roots supercharger and of its inherent advantages, it is concluded that this type is particularly attractive for use in certain classes of commercial airplanes and in a number of military types.
Date: January 1, 1928
Creator: Gardiner, Arthur W & Reid, Elliott G
Partner: UNT Libraries Government Documents Department

Preliminary free-flight investigation of the zero-lift drag penalties of several missile nose shapes for infrared seeking devices

Description: The results of a preliminary investigation to develop a nose shape suitable for housing an infrared seeker are presented. The zero-lift drag characteristics of a missile-like body with various unconventional nose shapes were obtained through a range of Mach numbers from 0.8 to 1.8 and Reynolds numbers, based on body length, from 20 x10 to the 6th power to 70 x 10 to the 6th power, respectively, by using rocket-propelled free-flight models. Results of the test indicate that at supersonic speeds about 70 percent of the drag penalty incurred by using spherical-tip nose shapes may be eliminated by using nose shapes which will still allow the seeker to function.
Date: December 9, 1952
Creator: Piland, Robert O
Partner: UNT Libraries Government Documents Department

Preliminary Free-Jet Performance of XRJ43-MA-3 Flight-Weight Ram-Jet Engine at Mach Numbers of 2.35, 2.50, and 2.70

Description: The performance of the XRJ43-MA-3 flight-weight ram-jet engine has been investigated in a free-jet facility as part of the development program for the "Bomarc," ram-jet powered, interceptor-type missile. The engine performance was obtained at Mach number s of 2.35, 2.50, and 2.70, altitudes from 50,000 to 75,000 feet, and Miami hot day and cold day inlet temperatures at an angle of attack of +4 deg. At each flight condition investigated, the engine control set an inner-ring fuel flow which was held constant as outer-ring fuel flow was varied. Combustion screech, which occurred more readily at the higher combustor pressures, fuel-air ratios, and inlet temperatures, resulted in discontinuities in the performance curves and an improvement in engine performance. The maximum time that the engine was allowed to operate continuously in the screech region was approximately 4 minutes. For these periods of time at the pressure levels investigated, no serious damage was evident. At a given fuel-air ratio, increasing the altitude or inlet temperature in the range investigated resulted in small reductions in net thrust coefficient. An increase in the flight Mach number raised the combustion efficiency but had little effect on the net thrust coefficient. Because conditions external to the engine did not simulate the actual flight conditions, no valid check of the durability of the combustion chamber and exhaust nozzle was obtained. All other engine components operated satisfactorily at least for at total burning time of 5 hours and high fuel-air-ratio operation of 35 minutes.
Date: November 18, 1955
Creator: McAulay, John E. & Prince, William R.
Partner: UNT Libraries Government Documents Department

Preliminary free-jet performance of XRJ43-MA-3 ram-jet engine at a Mach number of 2.70

Description: Report discussing an investigation to determine the free-jet performance characteristics of the XRJ43-MA-3 20B3 ram-jet engine at a Mach number of 2.70 at several angles of attack, inlet temperatures, and fuel-air ratios. Information about the inlet supercritical mass-flow ratio, diffuser-outlet Mach number contours, and effect of angle of attack and inlet temperature on engine performance is provided.
Date: April 15, 1955
Creator: Welna, Henry J. & Campbell, Carl E.
Partner: UNT Libraries Government Documents Department

Preliminary Full-Scale Wind-Tunnel Investigation of Wing Ducts for Radiators, Special Report

Description: Wing ducts for liquid-cooled engine radiators have been investigated in the N.A.C.A. full-scale wind tunnel on a large model airplane. The tests were made to determine the relative merits of several types of duct and radiator installations for an airplane of a particular design. In the test program the principal duct dimensions were systematically varied, and the results are therefore somewhat applicable to the general problems of wing duct design, although they should be considered as preliminary and only indicative of the inherent possibilities.
Date: March 1938
Creator: Silverstein, Abe & Nickle, F. R.
Partner: UNT Libraries Government Documents Department