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Effects of mach number and reynolds number on the maximum lift coefficient of a wing of naca 230-series airfoil sections
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1947 |
| Description | Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps. Chordwise pressure-distribution measurements were made for all flap configurations.. Peak values of maximum lift coefficient were obtained at relatively low free-stream Mach numbers and, before critical Mach number was reached, were almost entirely dependent on Reynolds Number. Lift coefficient increased by increasing Mach number or deflecting flaps while critical pressure coefficient was reached at lower free-stream Mach numbers. |
| File Size | 21883936 |
| Page Count | 47 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930081927 |
| Archival Resource Key | ark:/13960/t2t481f4c |
| Language | English |
| Publisher Date | 1947-01-01 |
| Access Restriction | Open |
| Subject Keyword | Lift Coefficients - Airfoils - Naca 230 Mach Number Wind Tunnel Tests - Naca High-speed (16') Work Carried On At Lal Wind Tunnel Tests - Naca - Pressure (19') Work Carried On At Lal Pressure Distribution - Airfoils - Naca 230 Chordwise Reynolds Number Airfoils - Naca 230 - Characteristics Wing Flaps, Split Wing Flaps, Split - Full-span Vs Partial-span 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 |
