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Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees

Description: From Introduction: "The airfoil sections tested, which differ only in thickness ratio, were the NACA 64-006, 64-008, 64-010, and 641-012. Lift, drag, and pitching-moment data were obtained for Mach numbers of 0.3 to that for tunnel choke at angles of attack of -2^o to 31^o. The results of this investigation are reported herein."
Date: June 5, 1953
Creator: Wilson, Homer B., Jr. & Horton, Elmer A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of the NACA 0012, 64₂-015, and 64₃-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees

Description: An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic characteristics of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 airfoil sections. Data were obtained at Mach numbers from 0.3 to that for tunnel choke, at angles of attack from -2deg to 30deg, and with the surface. of each airfoil smooth-and with roughness applied at the leading edge.The Reynolds numbers of the tests ranged from 0.8 x 10(exp 6) to 4.4 x 10(exp 6). The results are presented as vari… more
Date: July 23, 1954
Creator: Critzos, Chris C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Description: From Introduction: "The aerodynamic characteristics of a series of 10-foot-diameter propellers are being investigated in the Langley 16-foot high-speed tunnel in a comprehensive propeller research program. Using high-critical-speed NACA 16-series airfoil sections (reference 1), these propellers are designed to have Betz minimum induced-energy loss loading (reference 2) for a blade angle of 45^o at the 0.7 radius, when used as a four-blade propeller operating at an advance ratio of approximately… more
Date: October 1, 1948
Creator: Solomon, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at high speeds of full-scale propellers having Clark Y blade sections

Description: From Introduction: "The single purpose of this paper is to make available the data obtained from tests of these two Clark Y section propellers as quickly as possible with no attempt being made to analyze the results or to compare them with other high-speed-propeller test results."
Date: October 26, 1948
Creator: Johnson, Peter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics at High Speeds of Full-Scale Propellers Having Different Shank Designs

Description: "Tests of two 10-foot-diameter two-blade propellers which differed only in shank design have been made in the Langley 16-foot high-speed tunnel. The propellers are designated by their blade design numbers, NACA 10-(5)(08)-03, which had aerodynamically efficient airfoil shank sections, and NACA 10-(5)(08)-03R which had thick cylindrical shank sections typical of conventional blades. The propellers mere tested on a 2000-horsepower dynamometer through a range of blade-angles from 20 degrees to 55 … more
Date: February 13, 1947
Creator: Maynard, Julian D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at Mach number 4.04 of a rectangular wing of aspect ratio 1.33 having a 6-percent-thick circular-arc profile and a 30-percent-chord full-span trailing-edge flap

Description: From Introduction: "The present report gives results at a Mach number of 4.04 of the part of the program concerned with flap controls at Mach numbers from 1.62 to 6.9."
Date: May 29, 1953
Creator: Dunning, Robert W. & Ulmann, Edward F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls

Description: From Introduction: "The present paper contains the results of the investigation of the aerodynamic characteristics at Mach number of 2.01 of the two cruciform wing missiles equipped with larger canard controls and compares the result with that obtained previously with a smaller control."
Date: August 30, 1954
Creator: Spearman, M. Leroy & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Description: Report presenting an investigation at Mach number 4.06 on a typical supersonic airplane model with a 40 degree sweptback wing. The purpose of the investigation was to determine the effectiveness of using wedges on the body and on the vertical tail to increase the static directional stability. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: December 3, 1957
Creator: Dunning, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at Mach numbers 2.36 and 2.87 of an airplane configuration having a cambered arrow wing with a 75 degree swept leading edge

Description: From Introduction: "The results obtained in the wind-tunnel tests at Mach numbers 2.36 and 2.87 for several configurations utilizing this wing, including results on the wing alone are presented."
Date: August 4, 1958
Creator: Hallissy, Joseph M., Jr. & Hasson, Dennis F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test

Description: Report presenting flight testing of a rocket-propelled model of a typical multiengine airplane configuration to obtain data on drag, stability, and nacelle performance. Data were obtained at a variety of Mach numbers, lift coefficients, and subsonic and supersonic speeds. Results regarding airplane performance, nacelle performance, longitudinal characteristics, and lateral characteristics are provided.
Date: September 2, 1955
Creator: Chapman, Rowe, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics at Mach Numbers From 2.5 to 3.5 of a Canard Bomber Configuration Designed for Supersonic Cruise Flight

Description: Report presenting an investigation of a canard-type configuration designed for supersonic cruise flight in the Unitary Plan wind tunnel. Tests were conducted over a range of angles of attack and angles of sideslip. Results regarding the effect of forebody configuration, effects of Reynolds number and transition, effect of canard and elevon deflection, and effect of vertical surfaces are provided.
Date: September 10, 1958
Creator: Carmel, Melvin M.; Kelly, Thomas C. & Gregory, Donald T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics at Mach Numbers of 1.61 and 2.01 of Various Tip Controls on the Wing Panel of a 0.05-Scale Model of a Martin XASM-N-7 (Bullpup) Missile: TED No. NACA AD 3106

Description: "An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the control effectiveness and hinge-moment characteristics of the Martin XASM-N-7 (Bullpup) missile. A half-scale wing panel was tested with a tip control having three different hinge-line locations. The tests were made over an angle-of-attack range from -10 to 10 degrees and a control-deflection range of -15 to 3 degrees" (p. 1).
Date: 1956~
Creator: Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness

Description: From Introduction: "A 12-percent-chord-thick wedge section and a reversed NACA 0012 section were chosen for these tests as they are representative of sections having no boat tailing and appreciable boat tailing (i.e., blunt and rounded trailing edges, respectively), and the results of this investigation are compared with those obtained from a previous investigation of the NACA 0012 section. Conclusions are drawn regarding the relative merits of the two unconventional sections and the convention… more
Date: November 6, 1947
Creator: Eggers, A. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 1: maximum thickness at 20 percent of the chord

Description: From Summary: "This report presents the results of a wind-tunnel investigation conducted to determine the effects of Mach number on the aerodynamic characteristics of a wing of triangular plan form."
Date: November 19, 1948
Creator: Berggren, Robert E. & Summers, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 2: maximum thickness at midchord

Description: "The lift, drag, and pitching-moment characteristics of a triangular wing, having an aspect ratio of 2 and a symmetrical double-wedge profile of 5-percent-chord maximum thickness at midchord, have been evaluated from wind-tunnel tests at Mach numbers from 0.50 to 0.975 and from 1.09 to 1.49 and at Reynolds numbers ranging from 0.67 to 0.85 million. The lift, drag, and pitching-moment coefficients of the triangular wing with a leading-edge sweepback of approximately 63 degrees did not exhibit th… more
Date: December 3, 1948
Creator: Walker, Harold J. & Berggren, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Description: Report presenting an investigation at subsonic and transonic speeds in the high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of a 42.7 degree sweptback wing with a 20-percent-chord and 50-percent-span outboard aileron. The investigation was performed in transonic flow over a bump on the tunnel floor and in subsonic flow on one of the tunnel side walls.
Date: January 12, 1949
Creator: Turner, Thomas R.; Lockwood, Vernard E. & Vogler, Raymond D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-Body Combinations Having Cambered Wings With an Aspect Ratio of 3.5 and a Taper Ratio of 0.2: Effect at M = 2.01 of Nacelle Shape and Position on the Aerodynamic Characteristics in Pitch of Two Wing-Body Combinations with 47 Degree Sweptback Wings

Description: Memorandum presenting an investigation at M = 2.01 in the 4- by 4-foot supersonic pressure tunnel to determine the effect of a series of nacelles on the longitudinal stability characteristics of a sweptback wing-body combination. Nacelle shape and position were varied on a configuration with a 6-percent-thick wing with an aspect ratio of 3.5, a taper ratio of 0.2, and 47 degrees of sweep at the quarter chord.
Date: July 25, 1952
Creator: Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2: Effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.60 to determine the effects of sweep and thickness on the longitudinal characteristics of a series of wing-body combinations with cambered wings with an aspect ratio of 3.5 and taper ratio of 0.2. The results show the effects of sweep, thickness, and the horizontal canard surface on the lift, drag, and pitching-moment coefficients and lift-drag ratios. The lift-curve slope, aerodynamic-center loca… more
Date: January 10, 1952
Creator: Robinson, Ross B. & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2: Effects of sweep angle and thickness ratio on the static lateral stability characteristics at M = 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach number 2.01 to determine the effects of sweep angle and thickness ratio on the static lateral stability characteristics of a series of wings with taper ratio 0.2 and aspect ratio 3.5. The results are presented with little analysis.
Date: August 1, 1952
Creator: Hamilton, Clyde V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a 52.5 degree delta wing and a low, swept horizontal tail

Description: Report presenting a flight investigation over a range of Mach numbers to determine the aerodynamic characteristics at low lift of a rocket model of an airplane with a 52.5 degree delta wing of aspect ratio 3.08 and NACA 65A003 airfoil sections in the streamwise direction and a low, swept horizontal tail. Results regarding the longitudinal trim, lift, drag, longitudinal static stability, damping in pitch, and directional static stability are provided.
Date: March 29, 1954
Creator: Kehlet, Alan B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance: transonic-bump method

Description: Report presenting an investigation to determine the control hinge moments and effectiveness at transonic speeds of a delta wing equipped with a constant-chord flap-type control with and without an unshielded triangular horn balance in the 7- by 10-foot tunnel using the transonic-bump method. The data indicated that the horn balance control was consistently more effective in changing lift at all Mach numbers than was the plain control but there was no appreciable difference in pitching-moment ef… more
Date: September 16, 1952
Creator: Wiley, Harleth G. & Zontek, Leon
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance: transonic-bump method

Description: From Introduction: "Presented in this paper are the results of an investigation of a semispan model of a delta wing with 60^o sweepback at the leading edge which was equipped with a large triangular control having an overhang balance mounted on a skewed hinge axis. The purpose of this investigation was to determine the aerodynamic characteristics of a delta wing with a control which was designed to provide aerodynamic balance at zero control deflection based on the span load distribution of ref… more
Date: February 6, 1951
Creator: Wiley, Harleth G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge slats on the aerodynamic and longitudinal stability characteristics of a model of a swept-wing fighter-type airplane. Two different spanwise extents of leading-edge slats were tested, from 35 to 95 percent semispan and from 46 to 95 percent semispan. Results regarding the lift characteristics, drag characteristics and lift-drag ratios, stability characteristics, and flow-study pictures ar… more
Date: April 5, 1954
Creator: Runckel, Jack F. & Schmeer, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Full-Span Flap Type of Control With Overhang Balance: Transonic-Bump Method

Description: From Introduction: "This paper presents the aerodynamic characteristics of low-aspect-ratio sweptback wing having a full-span flap type of control employing an overhanging balance of 50 percent of the flap chord.The main purpose of this investigation was to determine if overhang balances are an effective means of reducing the hinge moments of flap type of controls at transonic speeds."
Date: January 25, 1952
Creator: Lockwood, Vernard E. & Hagerman, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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