1
Exercise 7: Maneuvering & High Speed Flight
For this week’s assignment you will research a historic or current fighter type aircraft of
your choice
(options for historic fighter jets include, but are not limited to: Me262, P-59, MiG-
15, F-86, Hawker Hunter, Saab 29, F-8, Mirage III, MiG-21, MiG-23, Su-7, Electric Lightning,
Electric Canberra, F-104, F-105, F-4, F-5, A-6, A-7, Saab Draken, Super Etendard, MiG-25,
Saab Viggen, F-14, and many more)
.
As previously mentioned and in contrast to formal research for other work in your
academic program at ERAU, Wikipedia may be used as a starting point for this
assignment. However, DO NOT USE PROPRIETARY OR CLASSIFIED INFORMATION even
if you happen to have access in your line of work.
Notice also that NASA has some great additional information at:
http://www.hq.nasa.gov/pao/History/SP-468/contents.htm.
1. Selected Aircraft:
2. Aircraft Gross Weight
[lbs]
:
3. Aircraft Wing Area
[ft
2
]
:
4. Positive Limit Load Factor (LLF - i.e. the max positive G) for your aircraft:
5. Negative LLF (i.e. the max negative G) for your aircraft:
6. Maximum Speed
[kts]
of your aircraft. If given as Mach number, convert by using Eq. 17.2
relationships with a sea level speed of sound of 661 kts.
For simplification, assume the CL
max
for your aircraft was 1.5 (unless you can find a
different CL
max
in your research).
A. Find the Stall Speed
[kts]
at 1G under sea level standard conditions for your aircraft (similar
to all of our previous stall speed work, simply apply the lift equation in its stall speed form from
page 44 to the above data):
B. Find the corresponding Stall Speeds for 2G, 3G, 4G, and so on for your selected aircraft (up
to the positive load limit from 4. above), using the relationship of Eq. 14.5. You can use the
table below to track your results.
C. Add the corresponding Stall Speeds for -1G, -2G, and so on for your selected aircraft (up to
the negative load limit from 5. above) to your table.
Assume that your fighter wing has
symmetrical airfoil characteristics, i.e. that the negative maximum CL value is equal but
opposite to the positive one.
(Feel free to use specific airfoil data for your aircraft, but please
make sure to use the correct maximum positive and negative Lift Coefficients in the correct
This document was developed for online learning in ASCI 309.
File name: Ex_5_Aircra± Performance
Updated: 08/01/2015