By D. E. HOAK
Different scans have badly lower mathematical formulation charts. this can be all fresh and usable , readable. there isn't any on the web at any place
FLIGHT C0NTROL DIVISION
AIR strength FLIGHT DYNAMICS LABORRATORY
WRIGHT PATTERSON AIR strength BASE OHIO
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Extra resources for USAF STABILITY AND CONTROL DATCOM
_5° ~ 3. 4. 2(£ cos a+ z sin a) (z cos a- £p b2 P P P = r sin a) (~Cy \ ~ ) Eq. 2-a V(WBH) 6. 6 M ,M 7. Linear-lift range 8. t 3. 4. 5. " ~ , +5° (loCy~) V(WBH) 9. Additional or identical tail limitations depend on ~Cy ) prediction method ( 13 V(WBH) --~-------------- Eq. 2-b (C, ,) WB (same limitations as for Eq. 2 l. f--- - - - + 2 ( 1-46 (No method) - ~Cn~)p (~Cy ~) V (WBHj . 1 - Test data - - -- -- -- -- -- -- -- ---- (C Eq. 2-c I , ) WB (same limitations as for Eq. 2-a) . and (loCI ) (~Cn ) .
5. 04, application to higher Mach numbers is acceptJble 6. Valid only on the plane of symmetry 7. Limitations de[Jend upon < ~A < 4 q" q~ a. ) CON FIG. g. 5 1. Linear-lift range (based on exposed wing geometry) (CLd)WB o 3. Triangular planforms Symmetric airfoils with conventional thickness distribution 4. 0< 5. 6. 0 ~A <4 KB(W) lbased on exposed wmg geometry) - q" qoo a. a" 7. 8. Conventional trapezoidal plan forms Valid only on the plane of symmetry 9. );' 10. II. 5 1. Straight-tapered wing 2.
Panel or by the interaction of the wing-root Mach cone with the wing tip. C' I. 9. 10. Ch 0 W SUBSONIC Ch = 0 A cos II. c/4 A + 2 cos II. I-a 4. High aspect ratios (A > 3) Ends of control surfaces parallel to plane of symmetry Neglects subcritical Mach-number effects Sealed, plain trailing-edge controls 5. 6. No separated flow Low speeds I. Symmetric. straight-sided controls Con:wl root and tip chords are parallel to the plane of symmetry Wing planform has leading edges swept ahead of Mach lines and has stream wise tips Controls are not influenced by tip conical flow from the opposite wing panel or by interaction of the wing-root Mach cone with the wing tip.