1954•NASA STI Repository (National Aeronautics and Space Administration)Requires access

Effects of subsonic Mach number on the forces and pressure distributions on four NACA 64A-series airfoil sections at angles of attack as high as 28 degrees

Louis S Stivers

Abstract

Report presenting lift, drag, moment, and pressure-distribution measurements for the NACA 64A010, 64A410, 64A006, and 64A406 airfoil sections at high subsonic Mach numbers. Results regarding lift characteristics, drag characteristics, moment characteristics, pressure distributions, characteristics within the local supersonic regions, and characteristics above the stall are provided.

About this research paper

What this paper is about

Why it matters

OpenAlex reports 22 citations for this work. Citation counts describe recorded attention and do not establish research quality.

Key contribution

A contribution statement is not available in the OpenAlex record.

Method / approach

Method details are not available in the OpenAlex metadata.

Main findings

Findings are not separately available in the OpenAlex metadata.

Limitations

Limitations are not available in the OpenAlex metadata.

Applications

Application details are not available in the OpenAlex metadata.

Available abstract

Key concepts: Airfoil, Mach number, Drag divergence Mach number, NACA airfoil, Angle of attack, Drag, Stall (fluid mechanics), Mechanics