Access
Serial/Series Title
Language
1 Matching Results
Results open in a new window/tab.
Results:
1 - 1 of
1
Tests of NACA 65(216)-420 and 66(218)-420 Airfoils at High Speeds
Report presenting wind tunnel tests of NACA 65(216)-420 and 66(218)-420 airfoils at speeds up to and slightly above the critical. Section coefficients of lift, drag, and pitching-moment and extensive pressure-distribution data are presented. The critical speed for these airfoils at their design life coefficient of 0.4 is shown to be about 460 miles per hour at seal level and about 415 miles per hour at 25,000 feet altitude.
Date:
April 10, 1944
Creator:
Anderson, Joseph L.
System:
The UNT Digital Library