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| Title: |
Dynamic stability derivatives at angles of attack from minus 5 deg to 90 deg for a variable-sweep fighter configuration with twin vertical tails
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| Author(s): |
Grafton, S. B.; Anglin, E. L.
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| Abstract: |
An investigation was conducted in the Langley full-scale tunnel to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -5 deg to 90 deg for a variable-sweep fighter configuration with twin vertical tails. The study consisted of forced-oscillation tests of a 1/10-scale model of the airplane at a Reynolds number of 0.4 million based on the reference wing mean aerodynamic chord. Tests were conducted for wing sweep angles of 22 deg, 35 deg, 50 deg, and 68 deg, and the effects of the vertical and horizontal tails, wing leading-edge slats, nose-mounted canards, and frequency of the oscillation were also evaluated.
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| NASA Center: |
Langley Research Center
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| Publication Date: |
Oct 1, 1972
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| Document Source: |
CASI |
| Online Source: |
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| Document ID: |
19720024394
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| Accession ID: |
72N32044
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| Publication Information: |
Number of Pages = 54 |
| Report Number: |
L-8426; NASA-TN-D-6909
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| Contract-Grant-Task Number: |
RTOP 501-17-01-06 |
| Price Code: |
A04 |
| Keywords: |
AERODYNAMIC CONFIGURATIONS; FIGHTER AIRCRAFT; STABILITY DERIVATIVES; WIND TUNNEL STABILITY TESTS; AERODYNAMIC CHARACTERISTICS; AIRCRAFT STABILITY; VARIABLE SWEEP WINGS;
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| Accessibility: |
Unclassified; No Copyright; Unlimited; Publicly available; |
| Updated/Added to NTRS: |
2008-09-15 |
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