MIG-21 THREAT TO U-2 AIRCRAFT

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP75B00285R000200070002-1
• Release Decision: RIPPUB
• Original Classification: T
• Document Page Count: 4
• Document Creation Date: December 22, 2016
• Document Release Date: June 8, 2010
• Sequence Number: 2
• Publication Date: August 3, 1965
• Content Type: MF

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IDEALIST
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3 August 1965
SIGNED
Lt. Colonel USAF
C/IDEA/OSA
IDEALIST
TOP SECRET
SUBJECT: MIG-21 Threat to U-2 Aircraft
1. Tests and computer/simulator studies have been under-
taken recently to determine U-2 vulnerability to the MIG-21
and to refine tactics to be employed by the U-2 to counter
the MIG-21 threat.
2. The tests, nicknamed "HUNGRY BOYS II", were conducted
on the West Coast in April and June 1965, utilizing F-104
and F-106 aircraft of the Air Defense Command and U-2 aircraft
of Detachment "G", Edwards AFB, California. Results of these
tests have been evaluated by the Office of Scientific Intelli-
gence, DD/S&T, but have not yet been published.
3. Studies are presently underway at Fort Worth, Texas
utilizing the MIG-21 simulator and analog, computer of the
General Dynamics Corporation and incorporating data derived
from the "HUNGRY BOYS II" tests.
4. Results of the tests and what is expected to be
achieved from the studies at Fort Worth will be discussed at
a meeting to be held in the OSA Control Center at 1400 local now,
on 6 Au u J65.
5. Addressees are invited to participate.
GROUP I
Exelu'ded from automatic
downgrading and
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C/IDEA/OSA/I :aea (3 Aug 65)
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PROJECT B65-7 DEMONSTRATION
This document contains the results obtained during the
demonstration on May 4, 1965. The results are for the System
13A effectiveness against the EWES/Analog simulation of the
SA-2 Missile System.
The significant points of interest for the demonstration
simulation are presented in Table 1. These parameters repre-
sent the values set in for-this demonstration. The radar cross
section reaches 100 square meters at some target aspect angles;
therefore, all parameters were set assuming this condition.
During the actual runs the radar cross section was programmed
as a function of the target aspect angle with respect to the
simulated FAN SONG radar.
The four flight 'paths used for the demonstration are
shown in Figure 1. These flight paths were programmed for a
simulated altitude of 70,000 feet and a target speed of 650
feet per second.
The following definition for the maneuvers will help show
the philosophy for each:
Maneuver A - This represents a turn initiated by the
pilot immediately following the detection of missile
guidance of a GUIDELINE missile. This turn was initiated
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