National Advisory Committee for Aeronautics (NACA) - 657 Matching Results

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Measurements of average heat-transfer and friction coefficients for subsonic flow of air in smooth tubes at high surface and fluid temperatures

Description: An investigation of forced-convection heat transfer and associated pressure drops was conducted with air flowing through smooth tubes for an over-all range of surface temperature from 535 degrees to 3050 degrees r, inlet-air temperature from 535 degrees to 1500 degrees r, Reynolds number up to 500,000, exit Mach number up to 1, heat flux up to 150,000 btu per hour per square foot, length-diameter ratio from 30 to 120, and three entrance configurations. Most of the data are for heat addition to … more
Date: December 31, 1950
Creator: Humble, Leroy V.; Lowdermilk, Warren H. & Desmon, Leland G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude performance characteristics of turbojet-engine tail-pipe burner with variable-area exhaust nozzle using several fuel systems and flame holders

Description: From Introduction: "The performance of several tail-pipe burners with fixed area exhaust nozzles is reported in references 1 to 4, and the performance of an NACA-designed tail-pipe burner with a variable-area exhaust nozzle is reported in reference 5. Operational characteristics of the tail-pipe burner are also discussed."
Date: December 29, 1950
Creator: Johnson, LaVern A. & Meyer, Carl L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical and analog studies of the effects of nonlinear stability derivatives on the longitudinal motions of an aircraft in response to step control deflections and to the influence of proportional automatic control

Description: Through theoretical and analog results the effects of two nonlinear stability derivatives on the longitudinal motions of an aircraft have been investigated. Nonlinear functions of pitching-moment and lift coefficients with angle of attack were considered. Analog results of aircraft motions in response to step elevator deflections and to the action of the proportional control systems are presented. The occurrence of continuous hunting oscillations was predicted and demonstrated for the attitude … more
Date: December 29, 1950
Creator: Curfman, Howard J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of Wing Loads at Mach Numbers Up to 0.87

Description: Report presenting flight measurements of the aerodynamic wing normal force, bending moment, and pitching moment using strain gains on the D-558-II airplane at Mach numbers up to 0.87 and angles of attack up to 38 degrees. Results regarding Mach number effects and normal-force-coefficient effects are provided.
Date: December 26, 1950
Creator: Mayer, John P.; Valentine, George M. & Swanson, Beverly J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a 42.7 Degree Sweptback Wing Model to Determine the Effects of Trailing-Edge Thickness on the Aileron Hinge-Moment and Flutter Characteristics at Transonic Speeds

Description: Report presenting an investigation in the high-speed tunnel of a 42.7 degree sweptback wing model to determine the effects of aileron trailing-edge thickness on aileron hinge moments and one-degree-of-freedom aileron flutter. Results regarding the hinge-moment characteristics and free-floating characteristics are also provided.
Date: December 26, 1950
Creator: Thompson, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Interpretation of boundary-layer pressure-rake data in flow with a detached shock

Description: From Summary: "A procedure is presented for determining boundary-layer quantities from pressure-rake data, which include the combined effects of viscous and shock losses. The problem is analyzed using schileren photographs of the shock configuration, the continuity of mass relationship, and the characteristic of the turbulent boundary layer that its outer edge is defined by a rapid change in slope in the Mach number profiles in the vicinity of the edge."
Date: December 22, 1950
Creator: Luidens, Roger W. & Madden, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Preliminary Experimental and Analytical Evaluation of Diborane as a Ram-Jet Fuel

Description: Report presenting an analytical and experimental evaluation of diborane as a ram-jet fuel, which seems to offer greater flight range, thrust, and combustion stability beyond what is attainable with petroleum fuels. Results regarding ideal thrust, stability, deposits, and flight range with several blends of diborane are provided.
Date: December 22, 1950
Creator: Gammon, Benson E.; Genco, Russell S. & Gerstein, Melvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of an End Plate on the Aerodynamic Characteristics of a 20.55 Degree Sweptback Wing with an Aspect Ratio of 2.67 and a Taper Ratio of 0.5.: Transonic-Bump Method

Description: "An investigation by the transonic-bump method conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effect of an end plate on the aerodynamic characteristics of a 20.55 degree sweptback wing with an aspect ratio of 2.67 and a taper ratio of 0.5 indicated that the end plate affected the aerodynamic characteristics of the wing at transonic Mach numbers in the same manner as has been observed for swept and unswept wings at low speeds" (p. 1).
Date: December 21, 1950
Creator: Watson, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of Three High-Recovery-Factor Thermocouple Probes for Room-Temperature Operation

Description: "Thermocouple probes have been designed to measure with small error the total temperature of gas moving at high velocities. Two major designed are presented: one is applicable to the construction of rakes and the other, of which there are two variations, can be used where exceptional accuracy is desired. The probes were calibrated in two jets; one jet exhausted into the atmosphere and the other into a pressure-controlled receiver" (p. 1).
Date: December 21, 1950
Creator: Scadron, Marvin D.; Gettelman, Clarence C. & Pack, George J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The External-Shock Drag of Supersonic Inlets Having Subsonic Entrance Flow

Description: Memorandum presenting a determination of the external-shock drags of supersonic inlets with circular cross sections from shadow photographs at a Mach number of 2.70 for a low-external-compression and a high-external-compression inlet. The calculated mass flow for both types of inlets showed reasonably good agreement with the measured values. Results as determined by the characteristics method and the approximate method are provided.
Date: December 20, 1950
Creator: Nucci, Louis M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lift and moment characteristics at subsonic Mach numbers of four 10-percent-thick airfoil sections of varying trailing-edge thickness

Description: Report presenting the results of a wind-tunnel investigation of the lift and moment characteristics of four 10-percent-thick circular-arc airfoil sections. Increases in the trailing-edge thickness were found to result in increases in maximum lift coefficient and lift-curve slope at all Mach numbers as well as increases in lift-divergence Mach number at all lift coefficients.
Date: December 20, 1950
Creator: Summers, James L. & Page, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Spontaneous ignition temperatures of pure hydrocarbons and commercial fluids

Description: From Summary: "The spontaneous ignition temperatures of 94 pure hydrocarbons and 15 fuels and commercial fluids were determined by a crucible method. The resulting data for the pure compounds are presented as functions of hydrocarbon structure."
Date: December 20, 1950
Creator: Jackson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude Performance Characteristics of Tail-Pipe Burner With Converging Conical Burner Section on J47 Turbojet Engine

Description: From Introduction: "The effect of flame-holder and fuel-system design on the burner performance and the effect of altitude and flight Mach number on over-all performance with a fixed-area exhaust nozzle are reported in reference 1 to 4. Altitude performance characteristics of a tail-pipe burner having a converging conical burner section are presented in this report. Tail-pipe burner performance at several flight conditions is given in both tabular and graphical forms and compared with performan… more
Date: December 19, 1950
Creator: Prince, William R. & McAulay, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF10F-1 Airplane

Description: "An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/30 - scale model of the Grumman XFlOF-1 airplane to determine its spin and recovery characteristics. The investigation included erect and inverted spins for both the straight-wing and swept-wing configurations. Tests to determine the optimum size spin-recovery parachutes and the rudder forces required for recovery were also made" (p. 1).
Date: December 18, 1950
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability and control characteristics of a 1/4-scale Bell X-5 airplane model in the landing configuration

Description: Report presenting an investigation of the static stability and control characteristics of a scale model of a preliminary Bell X-5 airplane design in the landing configuration with and without dive brakes. Results regarding the effects of slats, flaps, landing gear, gear doors, dive brakes and gap at the wing root are provided.
Date: December 18, 1950
Creator: Becht, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of Combustion-Chamber Performance on J47 Turbojet Engine

Description: From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."
Date: December 15, 1950
Creator: Campbell, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Matrix method of determining the longitudinal-stability coefficients and frequency response of an aircraft from transient flight data

Description: From Summary: "A matrix method is presented for determining the longitudinal-stability coefficients and frequency response of an aircraft from arbitrary maneuvers. The method is devised so that it can be applied to time-history measurements of combinations of such simple quantities as angle of attack, pitching velocity, load factor, elevator angle, and hinge moment to obtain the over-all coefficients. Although the method has been devised primarily for the evaluation of stability coefficients wh… more
Date: December 15, 1950
Creator: Donegan, James J. & Pearson, Henry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured in Flight on the Wing of the Douglas D-558-I Airplane for a 1 g Stall, a Speed Run to a Mach Number of 0.90, and a Wind-Up Turn at a Mach Number of 0.86

Description: "Tabulated pressure coefficients and aerodynamic characteristics are presented unanalyzed for six spanwise stations on the right wing of the Douglas D-558-I research airplane (BuAero No. 37972). The data were obtained in a 1 g stall at subcritical Mach numbers, in a speed run to a Mach number of 0.90 and in a wind-up turn at a Mach number of 0.86" (p. 1).
Date: December 15, 1950
Creator: Keener, Earl R. & Pierce, Mary
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of sweep on the damping-in-roll characteristics of three sweptback wings having an aspect ratio of 4 at transonic speeds

Description: Report presenting the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, an NACA 65A006 airfoil section, and three different sweep angles at a range of Mach numbers and angles of attack. The data were obtained in the 7- by 10-foot tunnel transonic bump by utilizing the twisted-wing technique. Results regarding the damping-in-roll parameter, angle of attack, and lift-curve slope are provided.
Date: December 14, 1950
Creator: Lockwood, Vernard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of methods for calculating dynamic lateral stability and response and for estimating aerodynamic stability derivatives

Description: "A summary of methods for making dynamic lateral stability and response calculations and for estimating the aerodynamic stability derivatives required for use in these calculations is presented. The processes of performing calculations of the time histories of lateral motions, of the period and damping of these motions, and of the lateral stability boundaries are presented as a series of simple straightforward steps. Existing methods for estimating the stability derivatives are summarized and, … more
Date: December 13, 1950
Creator: Campbell, John P. & McKinney, Marion O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary report of results obtained during demonstration tests of the Northrop X-4 airplanes

Description: Report presenting results during demonstration flight tests of the Northrop X-4 No. 1 and No. 2 airplanes. Results regarding the static and dynamic longitudinal- and lateral-stability characteristics, the stalling characteristics, and the buffet boundary.
Date: December 13, 1950
Creator: Sadoff, Melvin & Sisk, Thomas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - trailing-edge flaps deflected

Description: Report presenting aerodynamic characteristics of an unswept wing with an aspect ratio of 2.67, a taper ratio of 0.5, and employing full-span, 25-percent chord, plain, trailing-edge flaps using wind-tunnel testing of a semispan model. The trailing-edge flap was generally effective in changing the lift coefficient at each angle of attack and Mach number of the investigation. Results regarding lift characteristics, hinge-moment characteristics, drag characteristics, and pitching-moment characteris… more
Date: December 13, 1950
Creator: Stivers, Louis S., Jr. & Malick, Alexander W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. 3: analysis of force distribution at angle of attack (stabilizing fins removed)

Description: Report presenting an analysis of the force distribution on a slender pointed body of revolution at angle of attack utilizing pressure-distribution data and balance measurements. The data were obtained in the supersonic tunnel at a variety of Mach numbers and angles of attack. Results regarding normal forces and axial force are provided.
Date: December 12, 1950
Creator: Luidens, Roger W. & Simon, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the downwash and wake behind a triangular wing of aspect ratio 4 at subsonic and supersonic Mach numbers

Description: Report presenting the effects of Mach number between 0.50 and 0.95 and between 1.09 and 1.29 on the characteristics of the downwash and on the location of the wake behind a triangular wing of aspect ratio 4 as determined from semispan model tests.
Date: December 12, 1950
Creator: Walker, Harold J. & Stivers, Louis S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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