NACA Research Memorandums

NACA Technical Reports

Erwin, John R
Emery, James C

January 1951

An investigation has been conducted to determine the influence of aspect ratio, boundary-layer contr...

Performance of NACA eight-stage axial-flow compressor designed on the basis of airfoil theory /

Sinnette, John T.
King, J. Austin.
Schey, Oscar W.
Aircraft Engine Research Laboratory.
United States. National Advisory Committee for Aeronautics.

The NACA has conducted an investigation to determine the performance that can be obtained from a mul...

Performance of NACA eight-stage axial-flow compressor at simulated altitude

King, J. Austin.
Regan, Owen W.
Aircraft Engine Research Laboratory.
United States. National Advisory Committee for Aeronautics.

An investigation has been conducted by the NACA to determine the design-performance characteristics ...

NACA Technical Notes

Herrig, L Joseph
Emery, James C
Erwin, John R

February 1957

A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...

Systematic Two-Dimensional Cascade Tests of NACA 65Series Compressor Blades at Low Speeds, NACA

L. Joseph Herrig
James C. Emery
John R. Erwin
At Low Speeds I
L. Joseph
Herrig James
John R. Erwin

January 1958

The performance of NACA 65-series compressor blade sections in cascade has been investigated systema...

Systematic Two-Dimensional Cascade Tests of NACA 65-Series Compressor Blades at Low Speeds

Herrig, L. Joseph
Erwin, John R.
Emery, James C.

September 1951

The performance of NACA 65-series compressor blade section in cascade has been investigated systemat...

NACA Research Memorandums

Dunavant, James C.
Emery, James C.
Walch, Howard C.
Westphal, Willard R.

December 1955

Two-dimensional porous-well cascade tests of the NACA 65- (l2Al0) 10 and NACA 65-(l2A2I8b)10 blade s...

Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade /

Westphal, Willard R.
Godwin, William R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1951

The comparison indicated that cascade data accurately predicted the turning angle and blade pressure...

Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds

Emery, James C
Erwin, John R
Herrig, L Joseph

A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...

NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results /

Schulze, Wallace M.
Ashby, George C.
Erwin, John R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

A typical axial-flow compressor rotor using NACA 65-series compressor blades was tested at low speed...

Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade

Westphal, Willard R
Godwin, William R

March 1957

An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...

Low-speed cascade investigation of loaded leading-edge compressor blades

Emery, James C

Six percent thick NACA 63-series compressor-blade sections having a loaded leading-edge A4K6 mean li...

NACA Technical Reports

Erwin, John R
Emery, James C

January 1951

An investigation has been conducted to determine the influence of aspect ratio, boundary-layer contr...

Performance of NACA eight-stage axial-flow compressor designed on the basis of airfoil theory /

Sinnette, John T.
King, J. Austin.
Schey, Oscar W.
Aircraft Engine Research Laboratory.
United States. National Advisory Committee for Aeronautics.

The NACA has conducted an investigation to determine the performance that can be obtained from a mul...

Performance of NACA eight-stage axial-flow compressor at simulated altitude

King, J. Austin.
Regan, Owen W.
Aircraft Engine Research Laboratory.
United States. National Advisory Committee for Aeronautics.

An investigation has been conducted by the NACA to determine the design-performance characteristics ...

NACA Technical Notes

Herrig, L Joseph
Emery, James C
Erwin, John R

February 1957

A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...

Systematic Two-Dimensional Cascade Tests of NACA 65Series Compressor Blades at Low Speeds, NACA

L. Joseph Herrig
James C. Emery
John R. Erwin
At Low Speeds I
L. Joseph
Herrig James
John R. Erwin

January 1958

The performance of NACA 65-series compressor blade sections in cascade has been investigated systema...

Systematic Two-Dimensional Cascade Tests of NACA 65-Series Compressor Blades at Low Speeds

Herrig, L. Joseph
Erwin, John R.
Emery, James C.

September 1951

The performance of NACA 65-series compressor blade section in cascade has been investigated systemat...

NACA Research Memorandums

Dunavant, James C.
Emery, James C.
Walch, Howard C.
Westphal, Willard R.

December 1955

Two-dimensional porous-well cascade tests of the NACA 65- (l2Al0) 10 and NACA 65-(l2A2I8b)10 blade s...

Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade /

Westphal, Willard R.
Godwin, William R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1951

The comparison indicated that cascade data accurately predicted the turning angle and blade pressure...

Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds

Emery, James C
Erwin, John R
Herrig, L Joseph

A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...

NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results /

Schulze, Wallace M.
Ashby, George C.
Erwin, John R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

A typical axial-flow compressor rotor using NACA 65-series compressor blades was tested at low speed...

Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade

Westphal, Willard R
Godwin, William R

March 1957

An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...

Low-speed cascade investigation of loaded leading-edge compressor blades

Emery, James C

Six percent thick NACA 63-series compressor-blade sections having a loaded leading-edge A4K6 mean li...

NACA Technical Reports

Erwin, John R
Emery, James C

January 1951

An investigation has been conducted to determine the influence of aspect ratio, boundary-layer contr...

Performance of NACA eight-stage axial-flow compressor designed on the basis of airfoil theory /

Sinnette, John T.
King, J. Austin.
Schey, Oscar W.
Aircraft Engine Research Laboratory.
United States. National Advisory Committee for Aeronautics.

The NACA has conducted an investigation to determine the performance that can be obtained from a mul...

Performance of NACA eight-stage axial-flow compressor at simulated altitude

King, J. Austin.
Regan, Owen W.
Aircraft Engine Research Laboratory.
United States. National Advisory Committee for Aeronautics.

An investigation has been conducted by the NACA to determine the design-performance characteristics ...

NACA Research Memorandums

Abstract

Extracted data

NACA Research Memorandums

Abstract

Extracted data

Related items

Related items