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Serial/Series Title:
NACA Aircraft Circulars
Serial/Series Title:
NACA Wartime Reports
Collection:
Technical Report Archive and Image Library
Correlation of Wright Aeronautical Corporation cooling data on the R-3350-14 intermediate engine and comparison with data from the Langley 16-foot high-speed tunnel
Date: July 1, 1946
Creator: Pinkel, Benjamin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62698/
Paths of target-seeking missiles in two dimensions
Date: July 1, 1946
Creator: Watkins, Charles E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62682/
Parameters determining performance of supersonic pilotless airplanes powered by ram-compression power planes
Date: June 1, 1946
Creator: Hill, Paul R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62640/
Investigations on laminar boundary-layer stability and transition on curved boundaries
Date: May 1, 1946
Creator: Liepmann, Hans W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62701/
Stability and control force tests of four- and six-unit wing designs of low aspect ratio and 20 degree triangular plan form
Date: May 1, 1946
Creator: Varney, Elizabeth P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62680/
Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps
Date: April 1, 1946
Creator: Pardee, Otway O'm.
Description: Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61295/
Field of Flow About a Jet and Effect of Jets on Stability of Jet-Propelled Airplanes
Date: April 1, 1946
Creator: Ribner, Herbert S.
Description: A theoretical investigation was conducted on jet-induced flow deviation. Analysis is given of flow inclination induced outside cold and hot jets and jet deflection caused by angle of attack. Applications to computation of effects of jet on longitudinal stability and trim are explained. Effect of jet temperature on flow inclination was found small when thrust coefficient is used as criterion for similitude. The average jet-induced downwash over tail plane was obtained geometrically.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62555/
Approximate formulas for the computation of turbulent boundary-layer momentum thicknesses in compressible flows
Date: March 1, 1946
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62569/
Development of Wing Inlets
Date: March 1, 1946
Creator: Racisz, Stanley F.
Description: Lift, drag, internal flow, and pressure distribution measurements were made on a low-drag airfoil incorporating various air inlet designs. Two leading-edge air inlets are developed which feature higher lift coefficients and critical Mach than the basic airfoil. Higher lift coefficients and critical speeds are obtained for leading half of these inlet sections but because of high suction pressures near exist, slightly lower critical speeds are obtained for the entire inlet section than the basic airfoil.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61340/
Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint
Date: March 1, 1946
Creator: Daum, Fred L.
Description: Wing section outboard of flap was tested by wake surveys in Mach range of 0.25 - 0.78 and lift coefficient range 0.06 - 0.69. Results indicated that minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach less than 0.67. Below Mach number at which compressibility shock occurred, variations in Mach of 0.2 had negligible effect on profile drag coefficient. Shock was not evident until critical Mach was exceeded by 0.025.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61323/