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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: Technical Report Archive and Image Library
The Supersonic Axial-Flow Compressor

The Supersonic Axial-Flow Compressor

Date: January 1, 1950
Creator: Kantrowitz, Arthur
Description: An investigation has been made to explore the possibilities of axial-flow compressors operating with supersonic velocities into the blade rows. Preliminary calculations showed that very high pressure ratios across a stage, together with somewhat increased mass flows, were apparently possible with compressors which decelerated air through the speed of sound in their blading. The first phase of the investigation was the development of efficient supersonic diffusers to decelerate air through the speed of sound. The present report is largely a general discussion of some of the essential aerodynamics of single-stage supersonic axial-flow compressors. As an approach to the study of supersonic compressors, three possible velocity diagrams are discussed briefly. Because of the encouraging results of this study, an experimental single-stage supersonic compressor has been constructed and tested in Freon-12. In this compressor, air decelerates through the speed of sound in the rotor blading and enters the stators at subsonic speeds. A pressure ratio of about 1.8 at an efficiency of about 80 percent has been obtained.
Contributing Partner: UNT Libraries Government Documents Department
Extension of Useful Operating Range of Axial-Flow Compressors by Use of Adjustable Stator Blades

Extension of Useful Operating Range of Axial-Flow Compressors by Use of Adjustable Stator Blades

Date: January 1, 1948
Creator: Sinnette, John T & Voss, William J
Description: A theory has been developed for resetting the blade angles of an axial-flow compressor in order to improve the performance at speeds and flows other than the design and thus extend the useful operating range of the compressor. The theory is readily applicable to the resetting of both rotor and stator blades or to the resetting of only the stator blades and is based on adjustment of the blade angles to obtain lift coefficients at which the blades will operate efficiently. Calculations were made for resetting the stator blades of the NACA eight-stage axial-flow compressor for 75 percent of design speed and a series of load coefficients ranging from 0.28 to 0.70 with rotor blades left at the design setting. The NACA compressor was investigated with three different blade settings: (1) the design blade setting, (2) the stator blades reset for 75 percent of design speed and a load coefficient of 0.48, and (3) the stator blades reset for 75 percent of design speed and a load coefficient of 0.65.
Contributing Partner: UNT Libraries Government Documents Department
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
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: Parameters that enter into equation of trajectory of a missile are discussed. Investigation is made of normal pursuit, of constant, proportional, and line--of-sight methods of navigation employing target seeker, and of deriving corresponding pursuit paths. Pursuit paths obtained under similar conditions for different methods are compared. Proportional navigation is concluded to be best method for using target seeker installed in missile.
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
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