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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Serial/Series Title: NACA Wartime Reports
 Collection: National Advisory Committee for Aeronautics Collection
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

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 & Rubert, Kennedy F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Paths of target-seeking missiles in two dimensions

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
Parameters determining performance of supersonic pilotless airplanes powered by ram-compression power planes

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
Investigations on laminar boundary-layer stability and transition on curved boundaries

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
Stability and control force tests of four- and six-unit wing designs of low aspect ratio and 20 degree triangular plan form

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; Paulson, John W & Johnson, Joseph L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps

Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps

Date: April 1, 1946
Creator: Pardee, Otway O'm. & Heaslet, Max A.
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
Field of Flow About a Jet and Effect of Jets on Stability of Jet-Propelled Airplanes

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
Approximate formulas for the computation of turbulent boundary-layer momentum thicknesses in compressible flows

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
Development of Wing Inlets

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
Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint

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. & Zalovcik, John A.
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
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