The Flow and Force Characteristics of Supersonic Airfoils at High Subsonic Speeds

· ·
· National Advisory Committee for Aeronautics
E-raamat
15
lehekülge

Teave selle e-raamatu kohta

An investigation has been conducted at subsonic Mach numbers in the Langley rectangular high-speed tunnel on five supersonic airfoils and, for comparison, on two subsonic airfoils. Two-dimensional data were obtained by pressure measurements and schlieren photographs at angles of attack from 0 degrees to 4 degrees for Mach numbers between 0.30 and 0.90 for these 6-percent-thick symmetrical airfoils.

Hinnake seda e-raamatut

Andke meile teada, mida te arvate.

Lugemisteave

Nutitelefonid ja tahvelarvutid
Installige rakendus Google Play raamatud Androidile ja iPadile/iPhone'ile. See sünkroonitakse automaatselt teie kontoga ja see võimaldab teil asukohast olenemata lugeda nii võrgus kui ka võrguühenduseta.
Sülearvutid ja arvutid
Google Playst ostetud audioraamatuid saab kuulata arvuti veebibrauseris.
E-lugerid ja muud seadmed
E-tindi seadmetes (nt Kobo e-lugerid) lugemiseks peate faili alla laadima ja selle oma seadmesse üle kandma. Failide toetatud e-lugeritesse teisaldamiseks järgige üksikasjalikke abikeskuse juhiseid.

Rohkem autorilt W. F. Lindsey

Effects of Aspect Ratio on Air Flow at a High Subsonic Mach Numbers
W. F. Lindsey
Tasuta
Effect of Mach Number on Position Error as Applied to a Pitot-static Tube Located 0.55 Chord Ahead of an Airplane Wing
W. F. Lindsey
Tasuta
The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0
W. F. Lindsey
Tasuta
Effect of Compressibility on the Pressures and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-chord Flap
W. F. Lindsey
Tasuta

Sarnased e-raamatud

Effect of Mach Number on Position Error as Applied to a Pitot-static Tube Located 0.55 Chord Ahead of an Airplane Wing
W. F. Lindsey
Tasuta