Bo x 10-3 GO 40 'I 3O 2o 0 70 Relative gauge reading, in. 50 i_ ..... , .... IT if ......... i,_ ............................ 60 ' "" 4o 20 10 I i( . O 0 2 L_ -k m _m r A APPENDIX ORIGINAL PAGE IS OF POOR QUALITY -:q : 0.63 c : 16.8 in._...__ . , • . , t I i \ \ _ -L i___. L.fi % % r _ [ ' I . - I I , i m Data _n = 0.I0 _ Nine-point avg_c = 26.5 in. m v '] ,,, i ,i 4 6 8 iO _.2 14 16 IB 20 Distance along surface from L.E., in. (b) Upper surface of right winglet. Figure A7.-Concluded. 47 ®
_I 48 REFERENCES I. Loftin, Laurence K., Jr.: Subsonic Aircraft: Evolution and the Matching of Size to Performance. <strong>NASA</strong> RP-1060, 1980. 2. Stuper, J.: Investiqation of Boundary Layers on an Airplane Wing in Free Flight. NACA TM 751, 1934. 3. Jones, Melvill: Flight Experiments on the Boundary Layer. J. Aeronaut. Sci., vol. 5, no. 3, Jan. 1938, pp. 81-94. 4. Stephens, A. V.; and Haslam, J. A. G.: Flight Experiments on Boundary Layer Transition in Relation to Profile Drag. R. & M. No. 1800, British A.R.C., 1938. 5. Young, A. D.; and Morris_ D. E.: Note on Flight Tests on the Effect of Slip- stream on Boundary Layer Flow. R. & M. No. 1957, British A.R.C., 1939. 6. Young, A. D.; and Morris, D. E.: Further Note on Flight Tests on the Effect of Slipstream on Boundary Layer Flow. Rep. No. B.A. 1404b, British R.A.E., Sept. 1939. 7. Young, A. D.; Serby, J. E.; and Morris, D. E.: Flight Tests on the Effect of Surface Finish on Wing Drag. R. & M No. 2258, British A.R.C., 1939. 8. Goett, Harry J.; and Bicknell, Joseph: Comparison of Profile-Drag and Boundary- Layer Measurements Obtained in Flight and in the Full-Scale Wind Tunnel. NACA TN 693, 1939. 9. Bi@knell, Joseph: Determination of the Profile Drag of an Airplane Wing in Flight at High Reynolds Number_. NACA Rep. 667, 1939. 10. Wetmore, J. W.; Zalovcik, J. A.; and Platt, Robert C.: A Flight Investigation of the Boundary-Layer Characteristics and Profile Drag of the NACA 35-215 Laminar- Flow Airfoil at High Reynolds Numbers. <strong>NASA</strong> WR L-532, 1941. (Formerly NACA MR.) 11. Zalovcik, John A.: A Profile-Drag Investigation in Flight on an Experimental Fighter-Type Airplane - The North American XP-15 (Air Corps Serial No. 41-38). NACA ACR, Nov. 1942. 12. Serby, J. E.; Morgan, M. B.; and Cooper, E. R.: Flight Tests on the Profile Drag of 14% and 25% Thick Wings. R. & M. No_ 1826, British A.R.C., 1937. 13. Serby, J. E.; and Morgan, M. B.: Note on the Progress of Flight Experiments on Wing Drag. Rep. No. B.A. 1360, British R.A.E., Dec. 1936. 14. Tani, Itiro: On the Design of Airfoils in Which the Transition of the Boundary Layer is Delayed. NACA TM 1351, 1952._ 15. Zalovcik, John A.: Profile-Drag Coefficients of Conventional and Low-Drag Air- foils as Obtained in Flight. NACA WR L-139, 1944. (Formerly NACA ACR L4E31.)
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- Page 33 and 34: i< 1 11 APPENDIX SURFACE WAVINESS O
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- Page 49 and 50: 6O 50 40 30 20 iO 0 B0 50 40 Relati
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- Page 57 and 58: [ 52 m v ._ :_ ._ v o = "_" II x °
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98 _ z_ tt // /V (_ _, ORI_K/D,L, p
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loo 0 oi.._ L F-. 0 II ÷ 0 ORIGINA
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ii, _..:j ._t _ ....... 102 ORIGINA
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7, I!/ , T & / .J l i CL 1.2 1.0 0.
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i ORIGINAL PAGE |_] OF POOR QUALITY
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ORIGINAL PAGE IR OF POOR OUALITY I
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ORIQINAL PAGF..i_ OF POOR QUALITY 3
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112 0 e.o ORIGINAL PAGE IS OF POOR
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i., L-.. _A / 114 ORIGINAL PA(.._._
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116 .p 0 × o II \ II co H ¢) °¢
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_i-_ , ORIGI/NAL PAGE _9 OF POOR QU
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_20 i_' POOR QUALI'_( o_ ¢N I O 0
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122 OP POORQuALrry I ¢; _k _J o_ o
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i _. / ,p. _'- CO ¢t_ 4J ORIGINAL
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126 ORI_NAL PAGF. I_ OF POOR QUALIT
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L'_::; : • 128 ORi_NAI.,PAGEIB OF
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130 _e8 , • , ".4 Cp 0 .4 .8 z/c
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SECTION DRAG COEFFIClENT, 132 Cd .0
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I ,,, z/c 134 .O6 .05 .04 .03 .02 .
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i.- _ l! I' h . MINIGLOVE NLF GLOVE
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__ F_ Experimental transition ,| OR
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