Variable Camber Wing

Variable Camber Wing

Active / Technical Report | Accession Number: AD0911543 |

Abstract:

The initial series of wind tunnel tests which were designed to demonstrate the aerodynamic advantages of an advanced technology variable camber wing have been completed. These tests were conducted during twenty-four shifts of occupancy time at the NASA Ames 14-foot transonic wind tunnel between May 21 and June 15, 1973. The configurations tested consisted of the basic F-8, the F-8 with an advanced technology wing, the advanced wing with simple hinged leading and trailing edge flaps and various combinations of smooth, curved variable camber flaps. A summary of the test configurations and test conditions is presented.

Author(s):

No Author(s) Identified

Author Organization(s):

BOEING AEROSPACE CO SEATTLE WA

Descriptive Note:

Progress rept. no. 2 for period ending 15 Jun 1973

Pagination:

0025

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:

Approved For Public Release, Document Partially Illegible

Distribution Statement:

Approved For Public Release; Distribution Is Unlimited. Document Partially Illegible.

RECORD

Collection: TR

Identifying Numbers

Contract/Grant Number(s):

N00014-73-C-0244

Monitor Series:

ONR

Subject Terms

Joint Capability Areas:

JCA_1.2_Force Preparation; JCA_1_Force Support; JCA_1.2.6_Concepts; JCA_5.3_Planning; JCA_5_Command and Control

Communities of Interest:

Air Platforms

Descriptor(s):

*CAMBER, *LEADING EDGE FLAPS, LOAD DISTRIBUTION, MANEUVERABILITY, PERFORMANCE(ENGINEERING), MOMENTS, MODEL TESTS, TAKEOFF, JET FIGHTERS, FLAPS(CONTROL SURFACES), LIFT, ENGINEERING DRAWINGS, AIRCRAFT LANDINGS, FLUTTER, WIND TUNNEL MODELS, SWEPTBACK WINGS, TRANSONIC CHARACTERISTICS

Field(s)/Group(s):

Aerodynamics, Attack and Fighter Aircraft

Keyword(s):

*SUPERCRITICAL WINGS, *VARIABLE CAMBER WINGS, F 8 AIRCRAFT

Report Date:

1973 Jun 01