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 Collection: Technical Report Archive and Image Library
Results of flight tests to determine drag of parabolic and cone-cylinder bodies of very large fineness ratios at supersonic speeds

Results of flight tests to determine drag of parabolic and cone-cylinder bodies of very large fineness ratios at supersonic speeds

Date: August 30, 1951
Creator: Welsh, Clement J & Demoraes, Carlos A
Description: Results of a free-flight investigation at supersonic speeds to determine zero-lift drag of a series of bodies of revolution are presented. Configurations tested included two parabolic bodies with fineness ratios of 17.78 and 24.5 and two 8 degree cone-cylinder bodies with fineness ratios of 17.2 and 21.2. Results of previous tests of similar parabolic bodies but with lower fineness ratios are included in this paper for comparison. All bodies for which data are presented in this paper had a base-to-maximum-diameter ratio of 0.437. Calculated drag coefficients are shown for all bodies for which data are presented. (author).
Contributing Partner: UNT Libraries Government Documents Department
Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3

Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3

Date: June 16, 1952
Creator: Welsh, Clement J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of free-flight test of 1/10-scale model of the Convair XF2Y-1 airplane between Mach numbers of 0.7 and 1.45, including power-on flight at Mach number 1.2 : TED No. NACA DE 365

Results of free-flight test of 1/10-scale model of the Convair XF2Y-1 airplane between Mach numbers of 0.7 and 1.45, including power-on flight at Mach number 1.2 : TED No. NACA DE 365

Date: February 4, 1954
Creator: Bland, William M , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of initial wind-tunnel flutter experiments at low speed with a towed airplane model having a 40 degree sweptback wing of aspect ratio 3.62 equipped with pylon-mounted stores

Results of initial wind-tunnel flutter experiments at low speed with a towed airplane model having a 40 degree sweptback wing of aspect ratio 3.62 equipped with pylon-mounted stores

Date: March 24, 1955
Creator: Martina, Albert P & Young, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of landing tests of various airplanes

Results of landing tests of various airplanes

Date: September 1, 1942
Creator: Hootman, J A & Jones, A R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of measurements made during the approach and landing of seven high-speed research airplanes

Results of measurements made during the approach and landing of seven high-speed research airplanes

Date: February 4, 1955
Creator: Stillwell, Wendell H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of measurements of maximum lift and buffeting intensities obtained during flight investigation of the Northrop X-4 research airplane

Results of measurements of maximum lift and buffeting intensities obtained during flight investigation of the Northrop X-4 research airplane

Date: August 20, 1953
Creator: Baker, Thomas F
Description: The variation of the intensity of buffeting experienced throughout the operational region of the semitailless Northrop X-4 airplane and the values of maximum and peak normal-force coefficients in the Mach number range from 0.42 to 0.92 have been determined. The results are compared with data obtained with the swept-wing Douglas D-558-II airplane.
Contributing Partner: UNT Libraries Government Documents Department
Results of preliminary flight investigation of aerodynamic characteristics of the NACA two-stage supersonic research model RM-1 stabilized in roll at transonic and supersonic velocities

Results of preliminary flight investigation of aerodynamic characteristics of the NACA two-stage supersonic research model RM-1 stabilized in roll at transonic and supersonic velocities

Date: March 19, 1947
Creator: Pitkin, Marvin; Garner, William N & Curfman, Howard J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25

Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25

Date: April 6, 1948
Creator: Williams, W C & Beeler, De E
Description: Presents results of the U. S. Air Forces' accelerated transonic flight tests of the XS-1 No. 1 airplane for the Mach number range from 0.70 to 1.25 at altitudes from 30,000 to 49,000 feet. Data are included on horizontal-tail loads and buffeting, longitudinal trim changes, elevator effectiveness and control forces, and lateral trim characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Results of Primary Triangulation and Primary Traverse: Fiscal Year 1902-03

Results of Primary Triangulation and Primary Traverse: Fiscal Year 1902-03

Date: 1903
Creator: Gannett, Samuel S.
Description: From introduction: This report contains the results of the primary triangulation and primary traverse executed by the USGS during the fiscal year 1902-3.
Contributing Partner: UNT Libraries Government Documents Department
Results of Primary Triangulation and Primary Traverse: fiscal year 1903-04

Results of Primary Triangulation and Primary Traverse: fiscal year 1903-04

Date: 1904
Creator: Gannett, Samuel S.
Description: From introduction: This report contains the results of primary triangulation and primary traverse in the eastern and western divisions of the United States.
Contributing Partner: UNT Libraries Government Documents Department
Results of recent experiments with slotted wings

Results of recent experiments with slotted wings

Date: January 1, 1925
Creator: Lachmann, G
Description: This report gives the results of a recent series of experiments performed on a wing designed for a cantilever monoplane. Both wings were trapezial in their ground plan, with their tips rounded elliptically. These wing sections combine all known devices for increasing the lift, namely, the slot, the increased camber and angle of attack by means of an aileron running the whole length of the span. The last advance included in the wing section was an increase in wing area by means of an auxiliary wing adjusted by a sort of rectangular joint.
Contributing Partner: UNT Libraries Government Documents Department
Results of rocket model test of an airplane configuration having an arrow wing and slender flat-sided fuselage : lift, drag, longitudinal stability, lateral force, and jet effects at Mach numbers between 1.0 and 2.3

Results of rocket model test of an airplane configuration having an arrow wing and slender flat-sided fuselage : lift, drag, longitudinal stability, lateral force, and jet effects at Mach numbers between 1.0 and 2.3

Date: February 21, 1956
Creator: Peck, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of shear fatigue tests of joints with 3/16-inch-diameter 24S-T31 rivets in 0.064-inch-thick alclad sheet

Results of shear fatigue tests of joints with 3/16-inch-diameter 24S-T31 rivets in 0.064-inch-thick alclad sheet

Date: February 1, 1950
Creator: Holt, Marshall
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of tests on radiators for aircraft engines

Results of tests on radiators for aircraft engines

Date: January 1, 1920
Creator: Dickinson, H C; James, W S & Kleinschmidt, R V
Description: Part 1 is to present the results of tests on 56 types of core in a form convenient for use in the study of the performance of and possible improvements in existing designs. Working rules are given by which the data contained in the report may be used, and the most obvious conclusions as to the behavior of cores are summarized. Part 2 presents the results of tests made to determine the pressure necessary to produce water flows up to 50 gallons per minute through an 8-inch square section of radiator core. These data are of special value in evaluating the hydraulic head against which the circulating pump is required to operate.
Contributing Partner: UNT Libraries Government Documents Department
Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Date: January 14, 1947
Creator: Alexander, Sidney R.
Description: Tests to evaluate the effect of a conical windshield on the drag of a bluff body at supersonic speeds were performed for the following configurations: a sharp nose fuselage with stabilizing fins,a blunt nose fuselage with a hemispherical shape, and a blunt nose fuselage with a conical point. Results of the drag coeeficient are described at Mach 1.0 and the greatest Mach number of 1.37.
Contributing Partner: UNT Libraries Government Documents Department
Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90

Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90

Date: November 8, 1957
Creator: Dickens, W. L. & Hastings, E. C., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90 : TED No. NACA AD 3115

Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90 : TED No. NACA AD 3115

Date: November 8, 1957
Creator: Hastings, Earl C , Jr & Dickens, Waldo L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models

Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models

Date: January 7, 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Description: The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag.
Contributing Partner: UNT Libraries Government Documents Department
Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range

Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range

Date: January 1, 1957
Creator: Lauten, William T , Jr & Nelson, Herbert C
Description: Results of four thin, unswept, flutter airfoils attached to two freely falling bodies are reported. Two airfoils fluttered at a Mach number of 0.85, a third airfoil fluttered at a Mach number of 1.03, and a fourth fluttered at a Mach number of 1.07. Results of calculations of flutter speed using incompressible and compressible air-force coefficients, including a Mach number of 1.0, are presented.
Contributing Partner: UNT Libraries Government Documents Department
Results of UO₂ Diagnositic Tests for Run Beyond Cladding Breach in EBR-2

Results of UO₂ Diagnositic Tests for Run Beyond Cladding Breach in EBR-2

Date: 1979
Creator: Strain, R. V. & Lambert, J. D. B.
Description: Pre-defected uranium dioxide fuel elements were irradiated in EBR-II to determine the response of the fission-product-monitoring systems. In particular, the tests were performed to indicate whether the amount of oxide fuel exposed to the primary sodium could be estimated by monitoring, with the fuel-element-rupture detector (FERD), delayed neutrons (DN's) emitted from bromine and iodine isotopes in the sodium. Elements with defect areas of 0.005 and 0.20 cm sq. were irradiated consecutively in April and June 1977. Post-irradiation examination of the elements showed that an unexpectedly large amount of uranium dioxide/sodium chemical reaction occurred in the element with the 0.20-cm sq. defect.
Contributing Partner: UNT Libraries Government Documents Department
The results of wind-tunnel tests at low speeds of a four-engine propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

The results of wind-tunnel tests at low speeds of a four-engine propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

Date: December 21, 1953
Creator: Edwards, George G; Buell, Donald A & Dickson, Jerald K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

Date: September 1, 1956
Creator: Edwards, George G; Dickson, Jerald K; Sutton, Fred B & Demele, Frank A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Resume and analysis of NACA lateral control research

Resume and analysis of NACA lateral control research

Date: January 1, 1937
Creator: Weick, Fred E & Jones, Robert T
Description: An analysis of the principal results of recent NACA lateral control research is made by utilizing the experience and progress gained during the course of the investigation. Two things are considered of primary importance in judging the effectiveness of different control devices: the (calculated) banking and yawing motion of a typical small airplane caused by a deflection of the control, and the stick force required to produce this deflection. The report includes a table in which a number of different lateral control devices are compared on these bases.
Contributing Partner: UNT Libraries Government Documents Department