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Mach Number<br />
Mach Number<br />
<strong>Mig</strong>-<strong>21</strong>-FM-Identification-Rev. 14<br />
Altitude of 5,000m / 16,404ft<br />
1.000<br />
165<br />
0.95<br />
0.900<br />
127<br />
0.85<br />
0.800<br />
93<br />
0.75<br />
0.700<br />
62<br />
0.65<br />
0.600<br />
34<br />
0.55<br />
2<br />
0.500<br />
0.45<br />
0.400<br />
0.300<br />
0.200<br />
0.100<br />
0.000<br />
0.00 10.00 20.00 30.00 40.00 50.00 60.00 70.00 80.00 90.00 100.00 110.00 120.00 130.00 140.00 150.00 160.00 170.00 180.00<br />
Time (s)<br />
Extracted<br />
Sampled<br />
Mach<br />
V(TAS) dV/dt Ps Ps Thrust<br />
m/s (m/s**2) (m/s) (ft/s) (lbs)<br />
0.40 128 0.94 12 40 4,186<br />
0.50 160 1.00 16 54 4,186<br />
0.60 192 1.14 22 74 4,557<br />
0.70 224 1.03 24 78 4,654<br />
0.80 256 0.94 25 81 5,126<br />
0.90 288 0.84 25 81 6,346<br />
In this case, thrust computed for M=0.4 and 0.9 (first and last value) are questionable, because it is<br />
quite difficult to estimate the local acceleration before M0.4 and after M0.9<br />
Altitude of 7,000m / 22,966ft<br />
1.000<br />
0.900<br />
180<br />
0.85<br />
0.800<br />
134<br />
0.75<br />
0.700<br />
86<br />
0.65<br />
0.600<br />
38<br />
0.55<br />
0.500<br />
0.400<br />
Extracted<br />
Sampled<br />
0.300<br />
0.200<br />
0.100<br />
0.000<br />
0.00 10.00 20.00 30.00 40.00 50.00 60.00 70.00 80.00 90.00 100.00 110.00 120.00 130.00 140.00 150.00 160.00 170.00 180.00 190.00<br />
Time (s)<br />
Mach<br />
V(TAS) dV/dt Ps Ps Thrust<br />
m/s (m/s**2) (m/s) (ft/s) (lbs)<br />
0.50 156 0.38 6 20 3,248<br />
0.60 187 0.65 12 41 3,558<br />
0.70 <strong>21</strong>9 0.65 14 48 3,683<br />
0.80 250 0.68 17 57 4,125<br />
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