Purser, Paul E

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Copy No. 7R 
RM No . L7L22 
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RESEARCH MEMORANDUM 
EFFECT OF A PILOT'S CANOPY ON THE DRAG OF AN NACA RM -2 
DRAG RESEARCH MODEL IN FLIGHT AT TRANSONIC 
AND SUPERSONIC SPEEDS 
By 
Paul E. Purser 
Langley Memorial Aeronautical Laboratory 
Langley Field, Va. 
C~DC""'.JMENT 
CLASSIFICATION CHAMiID 'ro UNCLA 
~~oc,::en~;t~~o~=~/z;~r; AUTHORITY NAC! mEARCH ABSTRACT • 94 
')tate. within the mea.n!ng 'Clf the EsplOnac 
USC &>:31 ard 32. Ita lra.namisslon )r • 
revelatIon of it. content. 1n any m~l OUI , 
unaetheriZed penon I. pro>. btled." '-A fTI E· Jd 11 ' ;'56 
information ao clasSlfled may be 1m r."''' · I ...L 
:lnly to pe r 8Ur.1 in the mU\lAry and n 
services Qf the :;nil~ Slates, approprl f 
clvU1an ~leer. a.nd employees ~ the Fed.,r,l.,\ 
jovemment who have .. legitimate interest 
therein, and to 'Jl1Iled States citizens of kDDwn 
loyally and dlacr~wn. .... be- )f necessity mu.t be 
inf;:lTtned tberecf. 
NATIONAL ADVISORY COMMITTEE 
FOR AERONAUTICS 
WASHINGTON 
April 20, 1948 
https://ntrs.nasa.gov/search.jsp?R=19930085916 2020-06-17T16:25:18+00:00Z
NACA TIM No. L 7L22 CONFIDENTIAL 
NATIONAL ADVISORY COMMlTI'EE FOR AERONAUTICS 
RESEARCH MEMORANDUM 
EFFECT OF A PILOT I S CANOPY ON THE DRAG OF AN NACA RM-2 
DRAG RESEARCH MODEL IN FLIGHT AT TRANSONIC 
AND SUPERSONIC SPEEDS 
By Paul E. Purser 
1. Results of flight tests of an NACA RM-2 drag research model 
equipped with a pilot's canopy are presented for the Mach number range 
from 0.85 to 1.4. The corresponding Reynolds number range was from 
30 X 106 to 48 X 106 based on the over-all length of the model. The 
basic body was a pointed cylinder having a nose fineness ratio of 5.0~ 
an over-all fineness ratio of 12. 8~ and three stabilizing fins. The 
canopy was similar to those used on present-day high-speed airplanes, 
had a fineness ratio of about 7~ and added about 10 percent to the 
maximum frontal area of the body. Details of the model are shown in 
figures 1 to 3. 
2. The drag data were obtained by the Langley Pilotless-Aircraft 
Research Division at its testing station at Wallops Island~ Va., by 
means of the standard NACA RM-2 technique (reference 1) and are pre-
sented in figure 4. The canopy added an almost constant increment in 
drag coefficient of approximately 0.08 (based on the frontal area of 
the basic body, 0.1364 sq ft) in the Mach number range from 1.0 to 1.4. 
When the drag coefficients of the canopy-equipped model are based on the 
frontal area of that model (0.1511 sq ft), they are still 5 to 9 percent 
higher than for the basic model. 
Langley Memorial Aeronautical Laboratory 
National Advisory Committee for Aeronautics 
Langley Field, Va. 
REFERENCE 
1. Katz, Ellis R.: Results of Flight Tests at Supersonic Speeds to 
Determine the Effect of Body Nose Fineness Ratio on Body and Wing 
Drag. NACA RM No. L7B19, 1947. 
CONFIDENTIAL 
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CONFIDENTIAL 
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NACA RM No. L7L22 
CONFIDENTIAL 
(a) Top view. 
(b) Side view. 
CONFIDENTIAL (c) Three-quarter front view. 
Figure 3. - Photographs of NACA RM -2 model equipped with a 
pilot's canopy. 
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CONFIDENTIAL 
Fig ure 4.- [)rqq data for an NACA A/'1-2 model with and 
without pilots canopy. Rocket model fll'9ht tests. 
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Effect of a Pilot's Canopy on the Drag of an NACA RM-2 Drag Research Model in Flight at Transonic and Supersonic Speeds

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