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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Collection: Technical Report Archive and Image Library
Aerodynamic characteristics of 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Aerodynamic characteristics of 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Date: October 1949
Creator: Loftin, Laurence K , Jr & Smith, Hamilton A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Date: September 28, 1949
Creator: Martin, Andrew & Hunter, Harlo A.
Description: An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale moue1 of the Fairchild Lark missile, The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses. The wind-tunnel-test data indicate that rolling the missile 22.5 deg. had no serious effect on the static longitudinal stability. The desired maneuvering acceleration could not be attained with any of the horizontal wings tested, even with the horizontal wing flaps deflected 50 deg. The flaps on the 64A-209 wing (with small trailing-edge angles and flat sides) were effective at all flap deflections, while the flaps on the 16-series wings (with large trailing-edge angles) lost effectiveness at small flap deflections. The data showed that rolling moment existed when the vertical wing flaps were deflected with the model at other than zero angle of attack. A similar rolling moment probably would be found . with the horizontal wing flaps deflected and the model yawed.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage

Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage

Date: October 12, 1945
Creator: Schnurbusch, Alfred W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method

Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method

Date: March 4, 1949
Creator: Lina, Lindsay J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 42 degree swept-back wing with aspect ratio 4 and NACA 64(sub 1)-112 airfoil sections at Reynolds numbers from 1,700,000 to 9,500,000

Aerodynamic characteristics of a 42 degree swept-back wing with aspect ratio 4 and NACA 64(sub 1)-112 airfoil sections at Reynolds numbers from 1,700,000 to 9,500,000

Date: May 23, 1947
Creator: Neely, Robert H & Conner, D William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 45 degree swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections

Aerodynamic characteristics of a 45 degree swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections

Date: August 4, 1947
Creator: Proterra, Anthony J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody

Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody

Date: February 11, 1949
Creator: Macleod, Richard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections

Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections

Date: November 14, 1947
Creator: Loftin, Laurence K., Jr. & Cohen, Kenneth G.
Description: Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at three values of Reynolds number are presented for a group of NACA four-digit-series airfoil sections modified for high-speed applications. The effectiveness of flaps applied to these airfoils and the effect of standard leading-edge roughness were also investigated at one value of Reynolds number. Results are also presented of tests of three conventional NACA four-digit-series airfoil sections.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a number of modified NACA four-digit-series airfoil sections

Aerodynamic characteristics of a number of modified NACA four-digit-series airfoil sections

Date: June 1948
Creator: Loftin, Laurence K , Jr & Cohen, Kenneth S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Date: May 6, 1947
Creator: Perone, Angelo & Berthold, Cecil L.
Description: A Douglas C-74 airplane, during a test dive at about 0.525 Mach number, experienced uncontrollable longitudinal oscillations sufficient to cause shedding of the outer wing panels and the subsequent crash of the airplane. Tests of a section of the horizontal tail plane from a C-74 airplane were conducted in the Ames 16-foot high-speed wind tunnel to investigate the possibility of the tail as a contributing factor to the accident. The results of the investigations of fabric-covered elevators in various conditions of surface deformation are presented in this report.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a slot-lip aileron and slotted flap for dive brakes

Aerodynamic characteristics of a slot-lip aileron and slotted flap for dive brakes

Date: April 1941
Creator: Rogallo, F M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller

Date: September 2, 1948
Creator: Evans, Albert J & Salters, Leland B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a two-blade NACA 10-(3)(12)-03 propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(12)-03 propeller

Date: August 30, 1948
Creator: Allis, A E & Gray, W H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bumb method

Aerodynamic characteristics of a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bumb method

Date: April 21, 1949
Creator: Sleeman, William C , Jr & Becht, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Date: February 24, 1949
Creator: Goodson, Kenneth W & Weil, Joseph
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section

Date: November 1, 1949
Creator: Goodson, Kenneth W & Few, Albert G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Date: September 6, 1949
Creator: King, Thomas J , Jr & Myers, Boyd C , II
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section

Date: October 21, 1949
Creator: Goodson, Kenneth W & Morrison, William D , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of an 0.08-scale model of the Martin XB-51 Airplane at high subsonic speeds

Aerodynamic characteristics of an 0.08-scale model of the Martin XB-51 Airplane at high subsonic speeds

Date: October 7, 1949
Creator: Barnes, Robert H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of an airfoil-forebody swept flying-boat hull with a wing and tail swept back 51.3 degrees at the leading edge

Aerodynamic characteristics of an airfoil-forebody swept flying-boat hull with a wing and tail swept back 51.3 degrees at the leading edge

Date: September 9, 1949
Creator: Naeseth, Rodger L & Macleod, Richard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30

Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30

Date: November 10, 1948
Creator: Riebe, John M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of four NACA airfoil sections designed for helicopter rotor blades

Aerodynamic characteristics of four NACA airfoil sections designed for helicopter rotor blades

Date: February 1946
Creator: Rice, Fred J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels

Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels

Date: September 27, 1945
Creator: Klein, Milton M.
Description: Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections of the XF-12 airplane, were tested in the Langley two-dimensional low-turbulence tunnels to obtain their aerodynamic characteristics. Lift characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, 9,000,000, and 14,000,000, whereas drag characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, and 9,000,000. Pressure distributions were obtained for one of the root sections for several angles of attack at a Reynolds number of 2,600,000. Comparison of the root section that appeared best from the tests with the corresponding NACA 65-series section shows the Republic section has a higher maximum lift and higher calculated critical speeds, but a higher minimum drag. In addition, with standard roughness applied to the leading edge, the maximum lift of the Republic airfoil is lower than that of the NACA airfoil. Comparison of the Republic tip section with the corresponding NACA 65-series section shows the Republic airfoil has a lower maximum lift and a higher minimum drag than the NACA airfoil. The calculated critical speeds of the Republic section are slightly higher than those of the NACA section.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of horizontal tail surfaces

Aerodynamic characteristics of horizontal tail surfaces

Date: 1940
Creator: Silverstein, Abe & Katzoff, S
Description: Collected data are presented on the aerodynamic characteristics of 17 horizontal tail surfaces including several with balanced elevators and two with end plates. Curves are given for coefficients of normal force, drag, and elevator hinge moment. A limited analysis of the results has been made. The normal-force coefficients are in better agreement with the lifting-surface theory of Prandtl and Blenk for airfoils of low aspect ratio than with the usual lifting-line theory. Only partial agreement exists between the elevator hinge-moment coefficients and those predicted by Glauert's thin-airfoil theory.
Contributing Partner: UNT Libraries Government Documents Department