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Decade:
1940-1949
Serial/Series Title:
NACA Wartime Reports
Collection:
Technical Report Archive and Image Library
- Tests of the jet-motor air-intake duct system on a 1/4-scale stub-wing model of a pursuit-type airplane
- No Description digital.library.unt.edu/ark:/67531/metadc62023/
- Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane
- No Description digital.library.unt.edu/ark:/67531/metadc62050/
- A correlation of loadings and afterbody length-beam ratios of various flying-boat hulls
- No Description digital.library.unt.edu/ark:/67531/metadc61756/
- A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine II
- No Description digital.library.unt.edu/ark:/67531/metadc62296/
- The effect of liquid and ice particles on the erosion of a supercharger-inlet cover and diffuser vanes
- No Description digital.library.unt.edu/ark:/67531/metadc62087/
- Flight measurements by various methods of the drag characteristics of the XP-51 airplane
- No Description digital.library.unt.edu/ark:/67531/metadc61740/
- Investigation of ice formation in the induction system of an aircraft engine II : flight tests
- No Description digital.library.unt.edu/ark:/67531/metadc61815/
- Parameters determining performance of supersonic pilotless airplanes powered by ram-compression power planes
- No Description digital.library.unt.edu/ark:/67531/metadc62640/
- Progress report on strength and creep of special ceramic bodies in tension at elevated temperatures
- No Description digital.library.unt.edu/ark:/67531/metadc62220/
- The effect of a low-loss air valve on performance of a 22-inch-diameter pulse-jet engine
- No Description digital.library.unt.edu/ark:/67531/metadc62467/
- Aerodynamic characteristics of several modifications of a 0.45-scale model of the vertical tail of the Curtiss XP-62 airplane
- No Description digital.library.unt.edu/ark:/67531/metadc62683/
- An analysis of the indications of the University of Chicago airborne turbulence indicator in gusty air
- No Description digital.library.unt.edu/ark:/67531/metadc62668/
- Analysis of V-G Records from the SNB-1 Airplane
- Availability data obtained on SNB-1 trainer-class airplanes were analyzed and results presented as flight envelopes which predict occurrences of large values of air speed and acceleration. Comparison is made with SNJ-4 trainer-class airplane data analyzed by the same method. It is concluded that flight envelopes are satisfactory; that the two types show large differences in flight loads and speeds experience; and that SNB-1 will seldom, if ever, exceed design limit load factor and restricted speed, which SNJ-4 can be expected to exceed design-limit load factor and restricted speed in a very small number of flight hours. digital.library.unt.edu/ark:/67531/metadc62643/
- Correlation of Wright Aeronautical Corporation cooling data on the R-3350-14 intermediate engine and comparison with data from the Langley 16-foot high-speed tunnel
- No Description digital.library.unt.edu/ark:/67531/metadc62698/
- The effect of increase in combustion-air inlet temperature from 80 to 130 F on the sea-level performance of a 22-inch-diameter pulse-jet engine
- No Description digital.library.unt.edu/ark:/67531/metadc62549/
- Efficiency of a radial-flow exhaust-gas turbosupercharger turbine with a 12.75-inch tip diameter
- No Description digital.library.unt.edu/ark:/67531/metadc61860/
- Flight investigation of factors affecting the carburetor ram and nacelle drag of an A-26B airplane
- No Description digital.library.unt.edu/ark:/67531/metadc62684/
- Flight Investigation to Improve the Dynamic Longitudinal Stability and Control-Feel Characteristics of the P-63A-1 Airplane (AAF No. 42-68889) with Closely Balanced Experimental Elevators
- Results of flight tests of a control-feel aid presented. This device consisted of a spring and dashpot connected in series between the control stick and airplane structure. The device was tested in combination with an experimental elevator and bobweight which had given unsatisfactory dynamic stability and control-feel characteristics in previous tests. The control-feel aid effected marked improvement in both the control-feel characteristics and the control-feel dynamic longitudinal stability of the airplane. digital.library.unt.edu/ark:/67531/metadc61127/
- Paths of target-seeking missiles in two dimensions
- No Description digital.library.unt.edu/ark:/67531/metadc62682/
- A preliminary investigation of the icing characteristics of a large rectangular-throat pressure-type carburetor
- No Description digital.library.unt.edu/ark:/67531/metadc61816/
- A preliminary theoretical study of helicopter-blade flutter involving dependence upon coning angle and pitch setting
- No Description digital.library.unt.edu/ark:/67531/metadc61843/
- Air-flow and performance characteristics of engine-stage supercharger of a double-row radial aircraft engine II : effect of design variables
- No Description digital.library.unt.edu/ark:/67531/metadc62038/
- An Experimental Investigation of Flow Conditions in the Vicinity of an NACA D(Sub S)-Type Cowling
- Data are presented of the flow conditions in the vicinity of an NACA D sub S -type cowling. Tests were made of a 1/2 scale-nacelle model at inlet-velocity ratios ranging from 0.23 to 1.02 and angles of attack from 6 deg to 10 deg. The velocity and direction of flow in the vertical plane of symmetry of the cowling were determined from orifices and tufts installed on a board aligned with the flow. Diagrams showing velocity ratio contours and lines of constant flow angles are given. digital.library.unt.edu/ark:/67531/metadc62102/
- Wind-tunnel tests and analysis of three 10-foot-diameter three-blade tractor propellers differing in pitch distribution
- No Description digital.library.unt.edu/ark:/67531/metadc62189/
- Performance Charts for a Turbojet System
- Convenient charts are presented for computing the thrust, fuel consumption, and other performance values of a turbojet system. These charts take into account the effects of ram pressure, compressor pressure ratio, ratio of combustion-chamber-outlet temperature to atmospheric temperature, compressor efficiency, turbine efficiency, combustion efficiency, discharge-nozzle coefficient, losses in total pressure in the inlet to the jet-propulsion unit and in the combustion chamber, and variation in specific heats with temperature. The principal performance charts show clearly the effects of the primary variables and correction charts provide the effects of the secondary variables. The performance of illustrative cases of turbojet systems is given. It is shown that maximum thrust per unit mass rate of air flow occurs at a lower compressor pressure ratio than minimum specific fuel consumption. The thrust per unit mass rate of air flow increases as the combustion-chamber discharge temperature increases. For minimum specific fuel consumption, however, an optimum combustion-chamber discharge temperature exists, which in some cases may be less than the limiting temperature imposed by the strength temperature characteristics of present materials. digital.library.unt.edu/ark:/67531/metadc62466/
- Estimation of F-3 and F-4 knock-limited performance ratings for ternary and quaternary blends containing triptane or other high-antiknock aviation-fuel blending agents
- No Description digital.library.unt.edu/ark:/67531/metadc62293/