Email RIS file
Bookmark
Report an Issue

An Investigation of Flow Characteristics at Mach Number 4.04 over 6- and 9-percent-thick Symmetrical Circular-arc Airfoils Having 30-percent-chord Trailing-edge Flaps

Author:
Lord, Douglas R
Published:
July 19, 1951.
Physical Description:
1 electronic document
Additional Creators:
Ulmann, Edward F
Online Version

Availability

I Want It
I Want It

Finding items...

Restrictions on Access:
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary:
Section data obtained from wind-tunnel tests at Mach number 4.04 and Reynolds numbers of about 5.0 times 10 to the 6th power and 8.4 times 10 to the 6th power are presented for 6- and 9-percent-thick symmetrical circular-arc airfoils with 30 percent chord trailing-edge flaps. Pressure distributions, Schlieren photographs, and force and moment coefficients are included.
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 19930086615.
Accession ID: 93R15905.
NACA-RM-L51D30.
Terms of Use and Reproduction:
No Copyright.
View MARC record | catkey: 15431459