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Wind-tunnel investigation of a low-drag airfoil section with a double slotted flap
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1943 |
| Description | Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients. |
| File Size | 500959 |
| Page Count | 20 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930092793 |
| Archival Resource Key | ark:/13960/t2w40zv0k |
| Language | English |
| Publisher Date | 1943-01-01 |
| Access Restriction | Open |
| Subject Keyword | Airfoils - Naca 65,3-118-char , Moments & Ordinates Low-drag (wing Flaps, Slotte Wind Tunnel Tests - Naca - Low-turbulence (7 1/2' X 3') Wings-high-lift Devices Wind Tunnel Tests - Naca - Pressure, Low-turbulence (7 1/2' X 3') Wing Flaps, Slotted-double 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 |
