Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps

Description:

Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils.

Creator(s):
Creation Date: April 1, 1946
Partner(s):
UNT Libraries Government Documents Department
Collection(s):
National Advisory Committee for Aeronautics Collection
Technical Report Archive and Image Library
Usage:
Total Uses: 291
Past 30 days: 12
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Creator (Author):
Creator (Author):
Date(s):
  • Creation: April 1, 1946
Description:

Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils.

Language(s):
Subject(s):
Keyword(s): aerodynamics
Contributor(s):
Serial Title: NACA Wartime Reports
Serial Title: NACA Advanced Confidential Report
Partner:
UNT Libraries Government Documents Department
Collection:
National Advisory Committee for Aeronautics Collection
Collection:
Technical Report Archive and Image Library
Identifier:
Resource Type: Report
Format: Text
Rights:
Access: Public
Statement: No Copyright, Unclassified, Unlimited, Publicly available