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Transonic Wind-Tunnel Investigation of Effects of Windshield Shape and Canopy Location on the Aerodynamic Characteristics of Canopy-Body Combinations

Description: "Aerodynamic data have been obtained for a fuselage forebody alone and for canopy-body configurations consisting of four different canopies mounted on a fuselage forebody. Two of the canopies had the same shape and size rearward of the windshield but one had a "flat" and the other a "vee" windshield. The remaining two canopies were located at different body stations and were geometrically similar. The data indicated that the drag of the flat-windshield model was consistently lower than that of … more
Date: September 20, 1955
Creator: Cornette, Elden S. & Robinson, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Wing Size and Amount of Indentation on Applicability of Transonic Area Rule to Swept-Wing Configurations

Description: Memorandum presenting a systematic transonic zero-lift drag investigation utilizing a swept-wing configuration with three different ratios of wing to fuselage size utilizing a 6-inch helium gun. The experiments and comparisons with other results indicated that the reduction of pressure drag obtainable from partial indentation is approximately proportional to the amount of indentation employed up to a Mach number of 1.3. Results regarding the basic data, total drag, pressure drag, equivalent bod… more
Date: July 20, 1956
Creator: Hall, James Rudyard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Description: From Introduction: "The investigation reported herein was initiated to define further the effects on the aerodynamic characteristics and load distribution of a thin, sweptback wing of a low-pressure blowing system and also to provide information on which to base a more thorough study of a complete airplane configuration."
Date: September 20, 1955
Creator: Whittle, Edward F., Jr. & McLemore, H. Clyde
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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NACA Transonic Wind-Tunnel Test Sections

Description: Report presents an approximate subsonic theory for the solid-blockage interference in circular wind tunnels with walls slotted in the direction of flow. This theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.
Date: June 20, 1955
Creator: Wright, Ray H. & Ward, Vernon G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-Wedge Sections With the Maximum Thickness at 0.18 Chord

Description: Report presenting a program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section in the hypersonic tunnel at Mach number 6.9. The wings varied at semiapex angle and were tested over a range of angles of attack and Reynolds numbers. Results regarding lift and drag characteristics, center of pressure and moment coefficient, Schlieren photographs, and surface film flow studies are presented.
Date: October 20, 1954
Creator: Bertram, Mitchel H. & McCauley, William D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation to Determine Effects of Center-of-Gravity Location on the Transonic Flutter Characteristics of a 45 Degree Sweptback Wing

Description: Report presenting an experimental investigation in the transonic blowdown tunnel to determine effects of center-of-gravity location on the transonic flutter characteristics of a 45 degree sweptback-wing plan form of aspect ratio 4.0 and taper ratio 0.6. Solid-construction models with streamwise NACA 65A004 airfoil sections and center-of-gravity locations at three different chords were fluttered at a range of Mach numbers.
Date: February 20, 1956
Creator: Jones, George W., Jr. & Unangst, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tank investigation of the hydrodynamic characteristics of a 1/3.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with a revised forebody planing bottom : TED No. NACA DE 385

Description: From Summary: "Hydrodynamic characteristics have been determined for a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with the forebody modified so as to increase the depth of step and the angle between the forebody and afterbody keels. Longitudinal stability during takeoff and landing in smooth water and resistance of the complete model in smooth water and in waves are presented."
Date: October 20, 1955
Creator: Blanchard, Ulysse J. & Carter, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59

Description: Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a model of the Convair F-106A airplane with its fin tips retracted at a simulated altitude of 18,670 feet. Successful ejections of the rocket were made at supersonic speeds by applying a combination of ejection velocity and nose-down pitching moment at release.
Date: May 20, 1957
Creator: Lee, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58

Description: Report presenting a longitudinal stability and control investigation of a model of the Convair B-58 external store over a range of Mach numbers. Normal force, chord force, and static and dynamic stability derivatives are provided. Abrupt pitching disturbances were created by step-function movements of the canard surface.
Date: June 20, 1958
Creator: Hollinger, James A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59

Description: Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a Convair F-106A airplane. Results regarding pitching moment, ejections, release conditions, and missile trajectory are provided.
Date: May 20, 1957
Creator: Lee, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Drag Measurements of a 34 Degree Swept-Forward and Swept-Back NACA 65-009 Airfoil of Aspect Ratio 2.7 as Determined by Flight Tests at Supersonic Speeds

Description: Report presenting the results of flight testing to determine the zero-lift drag of an NACA 65-009 airfoil at a specified aspect ratio. The results are compared to previous testing of unswept and swept-back arrangements. The swept-forward and swept-back airfoils were found to produce lower values of zero-drag lift than the unswept airfoil.
Date: February 20, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination of Coupled Modes and Frequencies of Swept Wings by Use of Power Series

Description: "A solution is presented for the coupled modes and frequencies of swept wings mounted on a fuselage. The energy method is used in conjunction with power series to obtain the characteristic equations for both symmetrical and asymmetrical vibration. A numerical example which is susceptible to exact solution is presented, and the results for the exact solution and the solution presented in this paper show excellent agreement" (p. 1).
Date: October 20, 1947
Creator: Anderson, Roger A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of the effects of thickness ratio and aspect ratio on the drag of rectangular-plan-form airfoils at transonic speeds

Description: Report presenting testing conducted on two airfoils from a series of rectangular-plan-form airfoils of aspect ratios 7.6 and 5.1 and with NACA 65-006, 65-009, and 65-012 sections using the free-fall method. Results regarding the time histories, ground-velocity data, airfoil drag measurements, and drag coefficients are provided.
Date: June 20, 1947
Creator: Thompson, Jim Rogers & Mathews, Charles W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Lateral Control Characteristics as Measured in Abrupt Aileron Rolls at Mach Numbers Up to 0.86

Description: Report presenting flight measurements of the lateral control characteristics of the Douglas D-558-II airplane in abrupt rudder-fixed aileron rolls. Results regarding the aileron rolling effectiveness, time histories, and aileron effectiveness variation with Mach number are provided.
Date: July 20, 1950
Creator: Wilmerding, J. V.; Stillwell, W. H. & Sjoberg, S. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of Aileron Effectiveness of Bell X-1 Airplane Up to a Mach Number of 0.82

Description: "Abrupt, rudder-fixed aileron rolls have been made with the Bell X-1 airplane having a 10-percent-thick wing in glides to a Mach number of 0.82 at about 30,000 feet pressure altitude. Aileron movements were between one-fourth and one-half of full deflection. These aileron rolls indicate that Mach number has little effect on the aileron effectiveness up to a Mach number of 0.82" (p. 1).
Date: June 20, 1949
Creator: Drake, Hubert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Test of NACA FR-1-B, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research

Description: Report presenting testing of a low-acceleration transonic flutter test vehicle to obtain flutter data on two similar sweptback wings which indicated that wing flutter was symmetrical in mode. Results regarding flight and flutter characteristics for the FR-1-B are provided.
Date: July 20, 1948
Creator: Angle, Ellwyn E.; Clevenson, Sherman A. & Lundstrom, Reginald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Free-Flight Technique for Measuring Damping in Roll by Use of Rocket-Powered Models and Some Initial Results for Rectangular Wings

Description: Report presenting a simplified method for obtaining free-flight measurements of damping in roll through the use of rocket-powered models. Initial configurations have been tested for a range of Mach numbers. Results regarding the rolling velocity with two different airfoil sections and damping-in-roll coefficient are provided.
Date: December 20, 1949
Creator: Edmondson, James L. & Sanders, E. Claude, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The NACA 2000-horsepower propeller dynamometer and tests at high speed of an NACA 10-(3)(08)-03 two-blade propeller

Description: This paper contains a detailed description of a 2,000-horsepower propeller dynamometer used to make wind-tunnel tests of a two-blade NACA 10-(3)(08)-03 propeller for a range of blade angles from 20 degrees to 55 degrees at airspeeds up to 500 miles per hour. The results of these tests and comparisons with results obtained from a theoretical analysis and from previous tests made in other wind tunnels are presented.
Date: July 20, 1948
Creator: Corson, Blake W., Jr. & Maynard, Julian D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Extensible Wing-Tip Ailerons on an Untapered Semispan Wing at 0 Degree and 45 Degrees Sweepback

Description: Report presenting a low-speed wind-tunnel investigation to determine the lateral control characteristics of extensible wing-tip ailerons on an untapered semispan wing with two configurations; one was unswept and had an aspect ratio of 3.13 and the other was swept back 45 degrees and had an aspect ratio of 1.59. Results regarding the plain-wing aerodynamic characteristics and lateral control characteristics are provided.
Date: September 20, 1949
Creator: Hagerman, John R. & O'Hare, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane

Description: "Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configurations were simulated" (p. 1).
Date: April 20, 1950
Creator: Fisher, Lloyd J. & Morris, Garland J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal-Stability Investigation of High-Lift and Stall-Control Devices on a 52 Degree Sweptback Wing With and Without Fuselage and Horizontal Tail at a Reynolds Number of 6.8 X 10 (Exp 6)

Description: Contains low-speed longitudinal stability characteristics of a 52 degree sweptback wing of aspect ratio 2.88, taper ratio 0.625, and NACA 64 (sub 1)-112 airfoil sections normal to the 0.282-chord line, in combination with split flaps, leading-edge flaps, and upper-surface fences. Low-wing and midwing-fuselage aerodynamic characteristics are presented with and without a horizontal tail at various vertical locations. Tests were conducted at a Reynolds number of 6.8 x 10(exp 6).
Date: December 20, 1948
Creator: Foster, Gerald V. & Fitzpatrick, James E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of a pilot's canopy on the drag of an NACA RM-2 drag research model in flight at transonic and supersonic speeds

Description: Report presenting data from two experiments. One used the NACA RM-2 drag research model equipped with a pilot's canopy to determine the effect on aerodynamics. The other was conducted with the same configuration and returned similar results.
Date: April 20, 1948
Creator: Purser, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of high-lift and stall-control devices, fuselage, and horizontal tail on a wing swept back 42 degrees at the leading edge and having symmetrical circular-arc airfoils sections at a Reynolds number of 6.9 x 10(exp 6)

Description: Report presenting an investigation of the low-speed characteristics of a wing swept back 42 degrees at the leading edge and having various high-lift and stall-control devices and fuselage and horizontal tail vertical positions. Results regarding the characteristics of the basic wing, leading-edge flap investigation, wing fuselage investigation, and horizontal tail investigation are provided.
Date: April 20, 1949
Creator: Woods, Robert L. & Spooner, Stanley H.
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 D-558-I Research Airplane Through a Mach Number Range of 0.80 to 0.89 and Throughout the Normal-Force-Coefficient Range at Mach Numbers of 0.61, 0.70, 0.855, and 0.88

Description: "Tabulated pressure coefficients and aerodynamic characteristics obtained in flight from pressure distributions over six chordwise rows of orifices on the right wing of the D-558-I research airplane (BuAero No. 37972) are presented. The data were obtained through a Mach number range of 0.80 to 0.89 and throughout the normal-force-coefficient range at Mach numbers of 0.61, 0.70, 0.855, and 0.88. This paper supplements similar tabulated data which have been presented in NACA RM L50J10 and NACA RM… more
Date: August 20, 1951
Creator: Keener, Earl R. & Bandish, Rozalia M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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