NDLI: Critical mach numbers of thin airfoil sections with plain flaps

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Critical mach numbers of thin airfoil sections with plain flaps

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	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.
File Size	1084107
Page Count	27
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930092734
Archival Resource Key	ark:/13960/t0fv2wt0q
Language	English
Publisher Date	1946-01-01
Access Restriction	Open
Subject Keyword	Airfoils - Naca 651-208 - Characteristics Low-drag (wing Flaps) Airfoils - Naca - Characteristics Low-drag (wing Flaps) Airfoils - Naca 641-206 - Characteristics Low-drag (wing Flaps) Airfoils - Naca 641-210 - Characteristics Low-drag (wing Flaps) Airfoils - Naca 641-212 - Characteristics Low-drag (wing Flaps) Airfoils - Naca 651-206 - Characteristics Low-drag (wing Flaps) Airfoils - Naca 651-210 - Characteristics Airfoils, Thin Airfoils - Naca 641-208 - Characteristics Low-drag (wing Flaps) Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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