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A note on the drag due to lift of delta wings at mach numbers up to 2.0
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1953 |
| Description | In order to indicate the effects of Reynolds number and other variables on the drag due to lift of delta wings for Mach numbers up to 2.0, the results of several investigations of wing-body combinations employing delta wings with aspect ratios from 2 to 4 have been assembled for comparison. Effects of Reynolds number, leading-edge radius, and thickness ratio could be correlated with Reynolds number based on the leading-edge radius as a parameter. The results indicated that leading-edge Reynolds number effects were large at low speeds, but decreased with increases in Mach number. The effects of aspect ratio, wing modifications, and trim requirements are discussed. |
| File Size | 1263469 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930087537 |
| Archival Resource Key | ark:/13960/t5dc2cs9n |
| Language | English |
| Publisher Date | 1953-04-09 |
| Access Restriction | Open |
| Subject Keyword | Mach Number Effects - Complete Wings Wing-fuselage Combinations - Airplanes Reynolds Number Effects - Complete Wings Wings, Complete - Design Variables Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |