NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
The Development of Cambered Airfoil Sections Having Favorable Lift Characteristics at Supercritical Mach NumbersSeveral groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to have lift characteristics at supercritical Mach numbers which are favorable in the sense that the abrupt loss of lift, characteristic of the usual airfoil section at Mach numbers above the critical, is avoided. Aerodynamic characteristics determined, from two-dimensional windtunnel tests at Mach numbers up to approximately 0.9 are presented for each of the derived airfoils. Comparisons are made between the characteristics of these airfoils and the corresponding characteristics of representative NPiCA 6-series airfoils. The experimental results confirm the design expectations in demonstrating for the NACA S-series airfoils either no variation, or an Increase from the low-speed design value, In the lift coefficient at a constant angle of attack with increasing Mach number above the critical. It was not found possible to improve the variation with Mach number of the slope of the lift curve for these airfoils above that for the NACA 6-series airfoils. The drag characteristics of the new airfoils are somewhat inferior to those of the NACA 6- series with respect to divergence with Mach number, but the pitching-moment characteristics are more favorable for the thinner new sections In demonstrating somewhat smaller variations of moment coefficient with both angle of attack and Mach number. The effect on the aero&ynamic characteristics at high Mach numbers of removing the cusp from the trailing-edge regions of two 10-percent-chord-thick NACA 6-series airfoils is determined to be negligible.
Document ID
19930082444
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Note
Authors
Graham, Donald J (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
December 1, 1948
Subject Category
Aircraft Stability And Control
Report/Patent Number
NACA-TN-1771
Report Number: NACA-TN-1771
Accession Number
93R11734
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
AIRFOILS - NACA 836B110 - CHAR , MOMENTS & ORDINATES LOW-DRAG
AIRFOILS, CAMBERED
AIRFOILS - NACA 835A216 - CHAR , MOMENTS & ORDINATES LOW-DRAG
WIND TUNNEL TESTS - AAL - HIGH-SPEED ( 3 1/2'X 1')
AIRFOILS - NACA 836D110 - CHAR , MOMENTS & ORDINATES LOW-DRAG
AIRFOILS - NACA 836A110 - CHAR , MOMENTS & ORDINATES LOW-DRAG
AIRFOILS - NACA 847A1
AIRFOILS - NACA 836A216 - CHAR , MOMENTS & ORDINATES LOW-DRAG
AIRFOILS - NACA 836C110 - CHAR , MOMENTS & ORDINATES LOW-DRAG
AIRFOILS - NACA 847A216 - CHAR , MOMENTS & ORDINATES LOW-DRAG

Related Records

There are no records associated with this record.
No Preview Available
  NODES
Note 1