The Effect of Rate of Change of Angle of Attack on the Maximum Lift Coefficient of a Pursuit Airplane

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Abstract:

The effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane equipped with a low-drag-type wing has been investigated in stalls of varying abruptness over the Mach number range from 0.18 to 0.49 and Reynolds number range from 6.1 to 13.4 million. The maximum lift coefficients were found to increase linearly with increasing rate of change of angle of attack per chord length of travel up to the maximum rate attained in the tests 0.66 deg per chord length of travel in contradistinction to the results of the flight tests of two other airplanes. The tests indicated that the Mach and Reynolds numbers effects were of sufficient importance to produce more than a twofold variation in the increment of due to a given rate of change of angle of attack.

Author(s):
Gadeberg, Burnett L.
Author Organization(s):
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCHCENTER
Descriptive Note:
Technical note
Pagination:
0019

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
NACA-TN-2525
Monitor Series:
XD
 Subject Terms
Joint Capability Areas:
JCA_7.2.1_Mitigate Lethal Effects; JCA_7.2_Mitigate; JCA_7_Protection
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*ANGLE OF ATTACK, *AERODYNAMIC DRAG, *AERODYNAMIC LIFT, FLIGHT TESTING, MACH NUMBER, PURSUIT COURSES, WINGS, REYNOLDS NUMBER, DRAG REDUCTION
Field(s)/Group(s):
Aerodynamics
Keyword(s):
AQ M00 10 3107
Report Date:
1951 Oct 01
Creation Date:
2000 Aug 16