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NACA Radio Ground-Speed System for Aircraft, Special Report

Description: "A method that utilizes the Doppler effect on radio signals for determining the speed of an airplane and the distance traveled by the airplane has been developed and found to operate satisfactorily. In this method, called the NACA radio ground-speed system, standard readily available radio equipment is used almost exclusively and extreme frequency stability of the transmitters is not necessary. No complicated equipment need be carried in the airplane, as the standard radio transmitter is usuall… more
Date: February 1943
Creator: Hastings, Charles E.
Partner: UNT Libraries Government Documents Department
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Tests of a Highly Cambered Low-Drag-Airfoil Section with a Lift-Control Flap, Special Report

Description: Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-drag airfoil (NACA 65,3-618) with a plain flap designed for lift control. The results indicate that such a combination offers attractive possibilities for obtaining low profile-drag coefficients over a wide range of lift coefficients without large reductions of critical speed.
Date: December 1942
Creator: Abbott, Ira H. & Miller, Ralph B.
Partner: UNT Libraries Government Documents Department
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A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes

Description: "As an aid to airplane designers interested in providing pursuit airplanes with decelerating devices intended to increase the firing time when overtaking another airplane, formulas are given relating the pertinent distances and speeds in horizontal flight to the drag increase required. Charts are given for a representative parasite-drag coefficient from which the drag increase, the time gained, and the closing distance may be found. The charts are made up for three values of the ratio of the fi… more
Date: May 1942
Creator: Pearson, H. A. & Anderson, R. F.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Development of Ailerons for the Curtiss XP-60 Airplane, Special Report

Description: An investigation was made in the LWAL 7- by 10-foot tunnel of internally balanced, sealed ailerons for the Curtiss XP-60 airplane. Ailerons with tabs and. with various amounts of balance were tested. Stick forces were estimated for several aileron arrangements including an arrangement recommended for the airplane. Flight tests of the recommended arrangement are discussed briefly in an appendix, The results of the wind-tunnel and flight tests indicate that the ailerons of large or fast airplanes… more
Date: September 1942
Creator: Rogallo, F. M. & Lowry, John G.
Partner: UNT Libraries Government Documents Department
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Study of Turning Performance of a Fighter-Type Airplane Particularly as Affected by Flaps and Increased Supercharging, Special Report

Description: "Results of a study to determine the effects on turning performance due to various assumed modifications to a typical Naval fighter airplane are presented. The modifications considered included flaps of various types, both part and full space, increased supercharging, and increased wing loading. The calculations indicated that near the low-speed end of the speed range, the turning performance, as defined by steady level turns at a given speed, would be improved to some extent by any of the flap… more
Date: June 1942
Creator: Wetmore, J. W.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of an NACA Low-Drag Tapered Wing With Straight Trailing Edge and Simple Split Flaps, Special Report

Description: Report discusses the results of an investigation to determine the effect of the split flaps on the aerodynamic characteristics of the tapered wing. The results indicated that values of maximum lift coefficient obtained from the NACA low-drag sections are comparable to values obtained on tapered wings with conventional sections. The addition of split flaps did not appreciably alter the pattern of the stall.
Date: December 1941
Creator: Muse, Thomas C. & Neely, Robert H.
Partner: UNT Libraries Government Documents Department
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Determination of Flight Paths of an SBD-1 Airplane in Simulated Diving Attacks, Special Report

Description: An investigation has been made to determine the motions of and the flight paths describe by a Navy dive-bombing airplane in simulated diving attacks. The data necessary to evaluate these items, with the exception of the atmospheric wind data, were obtained from automatic recording instruments installed entirely within the airplane. The atmospheric wind data were obtained from the ground by the balloon-theodolite method. The results of typical dives at various dive angles are presented in the fo… more
Date: March 1943
Creator: Johnson, Harold I.
Partner: UNT Libraries Government Documents Department
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Tests of an NACA 66,2-420 Airfoil of 5-Foot Chord at High Speed, Special Report

Description: "This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds including the critical compressibility speed. Section coefficients of lift, drag, and pitching moment, and extensive pressure-distribution data are presented. The section drag coefficient at the design lift coefficient of 0.4 increased from 0.0042 at low speeds to 0.0052 at a Mach number of 0.56 (390 mph at 25,000 ft altitude). The critical Mach number was about 0.60. The results cover a Reynold num… more
Date: September 1942
Creator: Hood, Manley J. & Anderson, Joseph L.
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report

Description: "Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2" (p. 1).
Date: February 1943
Creator: Stack, John; Fedziuk, Henry A. & Cleary, Harold E.
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Aileron Characteristics of a Grumman F4F-3 Airplane

Description: "The aileron characteristics of a Grumman F4F-3 airplane were determined in flight by means of NACA recording and indicating instruments. The results show that the ailerons met NACA minimum requirements for satisfactory control throughout a limited speed range. A helix angle of approximately 0.07 radian was produced with flaps down at speeds from 90 to 115 miles per hour indicated airspeed and with flaps up from 115 to 200 miles per hour" (p. 1).
Date: September 1942
Creator: Kleckner, Harold F.
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of NACA Submerged-Duct Entrances

Description: The results of a preliminary investigation of submerged duct entrances are presented. It is shown that an entrance of this type possess desirable critical speed and pressure recovery characteristics when used on a fuselage or nacelle in a region of low incremental velocity and thin boundary layer. The data obtained indicate that submerged entrances are most suitable for use with internal-flow systems which diffuse the air only a small amount: for example, those used with jet motors which have a… more
Date: October 1945
Creator: Frick, Charles W.; Davis, Wallace F.; Randall, Lauros M. & Mossman, Emmet A.
Partner: UNT Libraries Government Documents Department
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Investigation of Flow in an Axially Symmetrical Heated Jet of Air

Description: The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air.
Date: December 1943
Creator: Corrsin, Stanley
Partner: UNT Libraries Government Documents Department
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Paths of Target Seeking Missiles in Two Dimensions

Description: Parameters that enter into equation of trajectory of a missile are discussed. Investigation is made of normal pursuit, of constant, proportional, and line--of-sight methods of navigation employing target seeker, and of deriving corresponding pursuit paths. Pursuit paths obtained under similar conditions for different methods are compared. Proportional navigation is concluded to be best method for using target seeker installed in missile.
Date: July 1946
Creator: Watkins, Charles E.
Partner: UNT Libraries Government Documents Department
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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

Description: Report presenting a comparison of the cooling-test data obtained on the identical Wright R-3350-14 engine equipped with the same cooling pressure-tube installation. The comparison reveals the large difference in cooling pressure drop that may be obtained in different test installations with the identical engine and pressure-tube installation because of an injudicious choice of pressure-tube locations.
Date: January 1945
Creator: Pinkel, Benjamin & Rubert, Kennedy F.
Partner: UNT Libraries Government Documents Department
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Cooling Tests of an Air-Cooled Engine Cylinder With Copper Fins on the Barrel

Description: Report presenting the results of comparative cooling tests run on two Wright C9GC (G-200) cylinders, one with the original steel fins and one with 1-inch spiral copper fins brazed on the barrel. Calculations were also performed using copper and aluminum fins with the same weight as the original steel fins, which showed positive results. Results regarding cylinder-temperature correlation, piston-temperature correlation, and comparative performance are also provided.
Date: July 1942
Creator: Sanders, J. C.; Wilsted, H. D. & Mulcahy, B. A.
Partner: UNT Libraries Government Documents Department
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Investigations on Laminar Boundary-Layer Stability and Transition on Curved Boundaries

Description: Report presenting an investigation of the transition of the boundary layer from the laminar to the turbulent region on a flat plate, on the concave and convex side of a plate with a 20-foot radius of curvature, and on the convex side of a plate with a 30-inch radius of curvature.
Date: May 1946
Creator: Liepmann, Hans W.
Partner: UNT Libraries Government Documents Department
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A summary of drag results from recent Langley full scale tunnel tests of Army and Navy airplanes

Description: Report presenting the results of a drag investigation of twelve military airplanes in order to increase their speed. The main purpose of the report is to point out undesirable aerodynamic features as a guide to airplane designers. Results regarding the power-plant installation, installations in wings, empennages, armament, canopies, and radio antenna are provided.
Date: February 1945
Creator: Lange, Roy H.
Partner: UNT Libraries Government Documents Department
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