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Wind-Tunnel Investigation at Transonic Speeds of a Jet Control on an 80 Degree Delta-Wing Missile

Description: Report presenting an investigation in the high speed tunnel of three missile models with cruciform delta wings swept back 80 degrees and equipped with jet controls to determine the effectiveness of the controls when using ram or mechanically compressed air. Results regarding the rolling characteristics, static rolling-moment coefficients, static pressure, and effect of the location of the jet control are provided.
Date: November 1, 1955
Creator: Turner, Thomas R. & Vogler, Raymond D.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing

Description: Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effectiveness of a spoiler-slot-deflector combination in producing rolling moments in the transonic speed range at angles of attack as high as 24 degrees over a range of Mach numbers. The wing had an aspect ratio of 4, a taper ratio of 0.6, an unswept quarter-chord line, and NACA 65A006 airfoil sections.
Date: December 8, 1953
Creator: Vogler, Raymond D.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Several Combinations of the Tail With Each of Two Foreshortened Body Segments

Description: "An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached … more
Date: July 14, 1950
Creator: Guy, Lawrence D. & Conner, D. William
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Tail Attached to a Segment of the Foreshortened Body

Description: "An investigation has been made of a partial-span model of the tail surface designed for use on the Hughes Falcon (MX-904) missile to determine the aerodynamic characteristics of the tail and elevator including elevator hinge moment. Data obtained at Mach numbers of 1.62 and 1.96 in the Langley 9- by 12-inch supersonic blowdown tunnel are presented for the condition where the tail was attached to a segment of the foreshortened body" (p. 1).
Date: May 4, 1950
Creator: Conner, D. William & Guy, Lawrence D.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a 1/5-Scale Model of the Ryan XF2R Airplane

Description: "Wind-tunnel tests on a 1/5-scale model of the Ryan XF2R airplane were conducted to determine the aerodynamic characteristics of the air intake for the front power plant, a General Electric TG-100 gas turbine, and to determine the stability and control characteristics of the airplane. The results indicated low-dynamic-pressure recovery for the air intake to the TG-100 gas turbine with the standard propeller in operation. Propeller cuffs were designed and tested for the purpose of improving the … more
Date: June 27, 1947
Creator: Wong, Park Y.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a 1/6-Scale Model of the Bumblebee XPM Missile at High Subsonic Speeds

Description: Report presenting an investigation of a model of the Bumblebee XPM missile to determine the causes of booster-fin failures for a range of Mach numbers and Reynolds numbers. The cause of fin failure was determined to be the launching shoes that caused the missiles to trim at increasingly negative angles of attack. Additional testing with wing spoilers and alternate booster fins was also conducted.
Date: December 11, 1950
Creator: Nelson, Warren H.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation of a 1/6-scale model of the Bumblebee XPM missile at high subsonic speeds

Description: Report presenting the results of an investigation of a model of the Bumblebee XPM missile to determine the causes of booster-fin failures on full-scale missiles. Results indicated that failures of the fins were due to launching shoes which caused the missile to try at increasingly negative angles of attack as the Mach number increased.
Date: December 11, 1950
Creator: Nelson, Warren H.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a 1/15-Scale Model of the Republic MX-1554 Airplane at Mach Numbers of 1.45 and 1.90

Description: "This report presents the results of a wind-tunnel investigation of a 1/15-scale model of the Republic MX-1554 airplane at Mach numbers of 1.45 and 1.90 and at a Reynolds number of 3.0 million based on the mean aerodynamic chord of the wing. Tests were conducted to determine the static longitudinal and lateral stability of the model and the control effectiveness of the all-movable tail, elevators, rudder, aileron, and spoiler. All the results of this investigation are presented in graphic form … more
Date: March 17, 1953
Creator: Smith, Willard G.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a 1/20-Scale Powered Model of a Four-Engine Transport Airplane

Description: Report presenting tests on a scale model of a four-engine transport airplane to determine the stability characteristics, empennage control-surface effectiveness, the effect of propeller rotation on longitudinal stability, and a method for carrying spare wing panels under the fuselage. The effect of two models of wing power operation on the characteristics of the model was studied. The results indicate that the model possess satisfactory stick-fixed longitudinal stability for all normal flight c… more
Date: May 30, 1944
Creator: Stevens, Victor I.; Douglass, William M. & Dods, Jules B., Jr.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a 1/60-Scale Model of the Republic MX-1554 Airplane at a Mach Number of 2.85

Description: Report presenting the results of an investigation to determine the static longitudinal and lateral stability and control characteristics of a model of the Republic MX-1554 airplane at a specified Mach and Reynolds number. No analysis was provided in the paper in order to expedite publication.
Date: March 18, 1953
Creator: Dickey, Robert R. & Spahr, J. Richard
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation of a 45 degree sweptback wing having a symmetrical root and a highly cambered tip, including the effects of fences and lateral controls

Description: Report presenting a wind-tunnel investigation conducted a range of Mach numbers of a 45 degree sweptback wing with varying camber along the span. Two other wings, one with no camber and one with uniform camber, were also tested. Results regarding the wing characteristics and control characteristics are provided.
Date: November 20, 1953
Creator: Cleary, Joseph W. & Boddy, Lee E.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Beveled Aileron Shape Designed to Increase the Useful Deflection Range

Description: Report presenting a wind tunnel investigation of a beveled aileron shape designed to increase the useful deflection range. The purpose of the investigation was to determine the general aerodynamic characteristics of this aileron and, in particular, to determine its useful angular range. Results regarding the effect of the hinge-gap seal, the surface condition and Reynolds number, and effect of aileron profile are provided.
Date: April 1944
Creator: Jones, R. T. & Underwood, W. J.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Full-Scale Model of the Hughes MX-904 Missile

Description: "A wind-tunnel investigation has been conducted to determine the stability and control characteristics of a full-size model of the Hughes MX-904 missile. Aerodynamic characteristics of the complete model through moderate ranges of angles of attack and yaw, with an additional test made through an angle of attack of 180 degrees, are presented. The effects of horizontal tail deflection are also included" (p. 1).
Date: 1950?
Creator: Wiley, Harleth G.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Full-Span Retractable Flap in Combination With Full-Span Plain and Internally Balanced Ailerons on a Tapered Wing

Description: Report discusses the results of an investigation into a full-span retractable flap in combination with a full-span plain and internally balanced ailerons on a tapered wing of a typical fighter airplane.The flap was designed to improve lateral control during high lifts for landing and take-off. The effects on the maximum life coefficient, aileron effectiveness, estimated rates of roll, and stick forces are provided.
Date: August 1943
Creator: Rogallo, F. M.; Lowry, John G. & Fischel, Jack
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a High-Critical-Speed Fuselage Scoop Including the Effects of Boundary Layer

Description: Report presenting a large air scoop designed for high critical speed, which has been tested in the 8-foot high-speed tunnel on the fuselage of a scale fighter-type airplane. The effects of boundary layer on scoop characteristics were found to be important at all inlet-velocity ratios. Results regarding the boundary-layer surveys, characteristics of original scoop installation, and characteristics of scoop with boundary-layer passage are provided.
Date: February 1945
Creator: Smith, Norman F. & Baals, Donald D.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Description: From Summary: "Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to… more
Date: September 1943
Creator: Bogdonoff, Seymour M.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Modified 1/20-Scale Model of the Convair MX-1554 Airplane at Mach Numbers of 1.41 and 2.01

Description: Report presenting an investigation of a model of the Convair MX-1554 airplane in the 4- by 4-foot supersonic pressure tunnel to evaluate the effects of extending the length of the fuselage afterbody and to provide longitudinal and lateral stability and control data. Results indicated that extension of the fuselage afterbody length caused little change in the minimum longitudinal force coefficient and drag due to lift.
Date: August 24, 1953
Creator: Hilton, John H., Jr. & Palazzo, Edward B.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Number of Total Pressure Tubes at High Angles of Attack: Subsonic speeds

Description: Report presenting a wind-tunnel investigation to determine the effect of inclination of the air stream on the measured pressures of 20 total-pressure tubes through a range of angles of attack and Mach numbers. Generally, the range of angle of attack over which the tubes remained insensitive to inclination was appreciably greater at supersonic speeds than at subsonic speeds.
Date: January 1951
Creator: Gracey, William; Coletti, Donald E. & Russell, Walter R.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack: Subsonic, Transonic, and Supersonic Speeds

Description: Note presenting the effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels. Results regarding effect of impact-opening size, effect of varying the shape of the internal chamber, effect of external shape, effect of slant profile, effect of venting of shielded tubes, effect of varying the probe position and the throat diame… more
Date: May 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack -- Subsonic, Transonic, and Supersonic Speeds

Description: "The effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes has been determined for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels at the Langley Aeronautical Laboratory" (p. 495).
Date: January 17, 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation of a plain aileron and a balanced aileron on a tapered wing with full-span duplex flaps

Description: Report presenting an investigation of a plain aileron and a balanced aileron on a tapered wing with full-span duplex flaps, which consisted of an inboard NACA slotted flap and an outboard balanced split flap. Increments of maximum lift coefficient of 0.82 and 1.04 were obtained from the inboard flap alone and from the duplex-flap combination.
Date: July 1942
Creator: Rogallo, F. M. & Lowry, John G.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation of a plain aileron with thickened and beveled trailing edges on a tapered low-drag wing

Description: Report presenting an investigation in the 7- by 10-foot tunnel of various modifications of the trailing-edge portion of a 0.20-chord plain aileron on a partial-span model of a tapered low-drag wing. The modifications tested included various amounts of symmetrical and unsymmetrical thickening and beveling of the aileron trailing edge. Results regarding coefficients and corrections, characteristics with ailerons neutral, characteristics with ailerons deflected, aileron trim characteristics, and e… more
Date: January 1943
Creator: Purser, Paul E. & McKee, John W.
Item Type: Refine your search to only Report
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