NASA-TN-D-6091-1971 Dynamic stability derivatives of a twin-jet fighter model for angles of attack from -10 degrees to 110 degrees《当攻角为-10至110时 双喷气战斗机模型的动态稳定性导数》.pdf
《NASA-TN-D-6091-1971 Dynamic stability derivatives of a twin-jet fighter model for angles of attack from -10 degrees to 110 degrees《当攻角为-10至110时 双喷气战斗机模型的动态稳定性导数》.pdf》由会员分享,可在线阅读,更多相关《NASA-TN-D-6091-1971 Dynamic stability derivatives of a twin-jet fighter model for angles of attack from -10 degrees to 110 degrees《当攻角为-10至110时 双喷气战斗机模型的动态稳定性导数》.pdf(39页珍藏版)》请在麦多课文档分享上搜索。
1、NASA TECHNICAL NOTE DYNAMIC STABILITY DERIVATIVES OF A TWIN-JET FIGHTER MODEL FOR ANGLES OF ATTACK FROM -100 TO 1100 . ., Langley Research Center Hampton, Va. 23365 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. JANUARY 1971 Provided by IHSNot for ResaleNo reproduction or networking
2、 permitted without license from IHS-,-,-TECH LIBRARY KAFB, NM 1. Report No. - “ NASA TN D-6091 “ 1 2. Government Accession No. 4. Title and Subtitle DYNAMIC STABILITY DERIVATIVES OF A TWIN-JET FIGHTER MODEL FOR ANGLES OF ATTACX FROM - 10 TO 110 7. Authorts) Sue B. Grafton and Charles E. Libbey “ - .
3、“ 9. Performing Organization Name and Address - “ NASA Langley Research Center Hampton, Va. 23365 . . 12. Sponsoring Agency Name and Address National Aeronautics and Space Administration Washington, D.C. 20546 “ 5. Supplementary Notes 1 3. Recipients 5. Report Date Januarv 1971 6. Performing Organiz
4、ation Code 8. Performing Organization Report No. L- 7370 10. Work Unit No. 126-63-11-36 *- 11. Contract or Grant No. 13. Type of Report and Period Covered Technical Note - . . . 14. Sponsoring Agency Code _ . “ .“ - . . 16. Abstract A low-speed investigation was conducted to determine the dynamic st
5、ability deriva- tives in pitch, roll, and yaw over an angle-of-attack range of -loo to 110 for a twin-jet swept-wing fighter model. Several frequencies and amplitudes were investigated to deter- mine the effects of these variables on the stability derivatives. The effect of the vertical and horizont
6、al tail, and horizontal-tail incidence on the derivatives was also evaluated. The results indicate that the model exhibited stable values of damping in pitch over the entire angle-of-attack range, but marked reductions of damping in roll were measured at the stall, and unstable values of damping in
7、yaw were present for the very high angles of attack asso- ciated with flat spins. Either removal of the horizontal or vertical tail or full up deflection of the horizontal tail eliminated the unstable characteristics of the damping-in-yaw derivatives. _ “ - - . . . 17. Key Words (Suggested by Author
8、is) ) Dynamic derivatives Fighter airplane - . 18. Distribution Statement Unclassified - Unlimited 19. Security Classif. (of this report) “ Security Classif. (of this page) Unclassified Unclassified 36 F 21. NO. of Pages 22. Price“ -“ _ “ =. . - For sale by the National Technical Information Service
9、, Springfield, Virginia 22151 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DYNAMIC STABILITY DERIVATIVES OF A TWIN-JET FIGHTER MODEL FOR ANGLES OF ATTACK FROM -loo TO llOo By Sue B. Grafton and Charles E. Libbey Langley Research Center SUMMARY A l
10、ow-speed investigation was conducted in the Langley full-scale tunnel to deter- mine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -loo to 110 for a twin-jet swept-wing fighter airplane. The study consisted of forced-oscillation tests of a 0.13-scale mode
11、l of the airplane at a Reynolds number of 1.33 x lo6. Several oscillatory frequencies and amplitudes were investigated to deter- mine the effects of these variables on the stability derivatives. The effects of the verti- cal and horizontal tail, and of the horizontal-tail deflection, on the derivati
12、ves were also evaluated. The results of the investigation indicated that the model exhibited stable values of damping in pitch over the entire angle-of-attack range, but marked reductions of damping in roll were measured at the stall, and unstable values of damping in yaw were present for the very h
13、igh angles of attack associated with flat spins. These unstable values of damping in yaw, which constitute propelling moments in a spin, were produced by aero- dynamic interference between the vertical and horizontal tails. Either removal of the horizontal or vertical tail or full up deflection of t
14、he horizontal tail eliminated the pro- pelling moments. INTRODUCTION The National Aeronautics and Space Administration is currently engaged in a research program to develop and validate theoretical methods for prediction of airplane stall and spin characteristics. A major portion of this program inv
15、olves correlation between theoretical calculations and data obtained by free-flight tests using dynamically scaled radio-controlled models of fighter airplanes. Previous theoretical and experimen- tal results obtained for a variable-sweep fighter with a long pointed nose are reported in reference 1.
16、 The present investigation was conducted to measure the dynamic stability deriva- tives of a twin-jet swept-wing fighter model over the angle-of-attack range associated with spinning; these data are intended to serve as aerodynamic input for additional Provided by IHSNot for ResaleNo reproduction or
17、 networking permitted without license from IHS-,-,-. . theoretical studies of the stall and spin characteristics of this particular configuration. The investigation consisted of forced-oscillation tests which were conducted over an angle-of-attack range from -loo to 110 and included the effects of f
18、requency and ampli- tude of the oscillatory motion. Tests were also conducted with the vertical and horizon- tal tails removed. The effect of horizontal-tail deflection on the yawing dynamic deriva- tives is also presented. Pertinent static force tests were conducted to aid in the analysis of the dy
19、namic data. SYMBOLS Physical Concepts The longitudinal and lateral-directional data presented herein are referred to the body-axis system (see fig. 1). All data are referred to a center-of-gravity position of 33-percent mean aerodynamic chord. In order to facilitate international usage of data prese
20、nted, dimensional quantities are presented both in the U.S. Customary Units and in the International System of Units (SI). Equivalent dimensions were determined by using the conversion factors given in reference 2. b wing span, ft (m) - C mean aero9namic chord, ft (m) - Ch mean aerodynamic chord of
21、horizontal tail, ft (m) FA force along X body axis, lb (N) FY force along Y body axis, lb (N) FN force along Z body axis, lb (N) f frequency of oscillation, cycles/sec k reduced-frequency parameter, - 2v wb for lateral-directional parameter or WC - - 2v for longitudinal parameter MX rolling moment,
22、ft-lb (m-N) 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-a! pitching moment, ft-lb (m-N) yawing moment, ft-lb (m-N) rolling velocity, rad/sec pitching velocity, rad/sec free-stream dynamic pressure, !?!f lb/ft2 (N/m2) 2 yawing velocity, rad/sec
23、components of resultant velocity VA along X, Y, and Z body axes, respectively, ft/sec (m/sec) free-stream velocity, ft/sec (m/sec) resultant linear velocity, ft/sec (m/sec) body reference axes angle of attack, deg or rad angle of sideslip, deg or rad horizontal-tail deflection, positive when trailin
24、g edge down, deg air density, slugs/ft3 (kg/m3) angle of pitch, deg or rad pitch-angle increment, deg angle of roll, deg or rad roll-angle increment, deg 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Q AQ w angle of yaw, deg or rad yaw-angle incr
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