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An investigation of the effects of a vortex-generator configuration on the aerodynamic characteristics of a 1/4-scale model of the x-1 airplane (10-percent-thick wing)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1952 |
| Description | An investigation of a vortex-generator configuration on the wings of a l/4-scale model of the X-1 airplane having a 10-percent-thick wing was conducted in the Langley 16-foot transonic tunnel. The effect of the vortex generators was determined by comparing the model aerodynamic characteristics, wing-pressure distributions, and wing-wake patterns for model configurations with and without vortex generators on the wings. Results are presented from tests at 0.1 increments in Mach number from about 0.69 to 0.99, at Reynolds numbers of about 4.1 x 10(exp 6) to 4.7 x 10(exp 6), and through an angle-of-attack range up to 1.5 deg at lower speeds and up to 5 deg at the highest speed. In general, little difference in the aerodynamic characteristics was observed, except at a Mach number of 0.90 where a rearward movement of the shock on the upper surface of the wing with the vortex generators installed resulted in less separation. |
| File Size | 1362021 |
| Page Count | 40 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20050041843 |
| Archival Resource Key | ark:/13960/t0gt9z158 |
| Language | English |
| Publisher Date | 1952-12-23 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control 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 |
