HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Reynolds number: 50,000 Max Cl/Cd: 33.3 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest3-il-50000.txt Download as CSV file: xf-tempest3-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4839 0.09774 0.09079 -0.0092 1.0000 0.3294
-8.500 -0.4807 0.09434 0.08744 -0.0084 1.0000 0.3421
-8.250 -0.4792 0.09104 0.08420 -0.0076 1.0000 0.3553
-8.000 -0.4790 0.08798 0.08120 -0.0064 1.0000 0.3713
-7.250 -0.6240 0.06325 0.05647 -0.0284 1.0000 0.1449
-7.000 -0.6439 0.05751 0.05006 -0.0262 1.0000 0.1241
-6.750 -0.6372 0.05371 0.04607 -0.0240 1.0000 0.1206
-6.500 -0.6324 0.04994 0.04204 -0.0215 1.0000 0.1177
-6.250 -0.6295 0.04602 0.03759 -0.0185 1.0000 0.1129
-6.000 -0.6235 0.04287 0.03361 -0.0149 1.0000 0.1088
-5.750 -0.6107 0.03966 0.02996 -0.0123 1.0000 0.1085
-5.500 -0.5958 0.03682 0.02660 -0.0098 1.0000 0.1090
-5.250 -0.5782 0.03427 0.02407 -0.0082 1.0000 0.1156
-5.000 -0.5605 0.03224 0.02144 -0.0058 1.0000 0.1228
-4.750 -0.5378 0.02978 0.01895 -0.0045 1.0000 0.1316
-4.500 -0.5153 0.02786 0.01683 -0.0030 1.0000 0.1488
-4.250 -0.4895 0.02572 0.01475 -0.0018 1.0000 0.1795
-4.000 -0.4654 0.02330 0.01288 -0.0006 1.0000 0.2552
-3.750 -0.4544 0.02050 0.01151 0.0027 1.0000 0.4209
-3.500 -0.1059 0.02259 0.01300 -0.0404 1.0000 1.0000
-3.250 -0.1012 0.02200 0.01225 -0.0384 1.0000 1.0000
-3.000 -0.0970 0.02152 0.01166 -0.0360 1.0000 1.0000
-2.750 -0.0936 0.02112 0.01117 -0.0332 1.0000 1.0000
-2.500 -0.0909 0.02081 0.01076 -0.0302 1.0000 1.0000
-2.250 -0.0888 0.02057 0.01042 -0.0270 1.0000 1.0000
-2.000 -0.0872 0.02039 0.01015 -0.0235 1.0000 1.0000
-1.750 -0.0855 0.02027 0.00994 -0.0200 1.0000 1.0000
-1.500 -0.0835 0.02020 0.00978 -0.0165 1.0000 1.0000
-1.250 -0.0808 0.02018 0.00963 -0.0130 1.0000 1.0000
-1.000 -0.0771 0.02020 0.00956 -0.0097 1.0000 1.0000
-0.750 -0.0723 0.02027 0.00953 -0.0066 1.0000 1.0000
-0.500 -0.0663 0.02039 0.00955 -0.0037 1.0000 1.0000
-0.250 -0.0590 0.02055 0.00962 -0.0010 1.0000 1.0000
0.000 -0.0508 0.02075 0.00973 0.0015 1.0000 1.0000
0.250 -0.0416 0.02099 0.00990 0.0037 1.0000 1.0000
0.500 -0.0317 0.02128 0.01010 0.0058 1.0000 1.0000
0.750 -0.0212 0.02161 0.01036 0.0078 1.0000 1.0000
1.000 -0.0102 0.02199 0.01068 0.0095 1.0000 1.0000
1.250 0.0013 0.02240 0.01106 0.0111 1.0000 1.0000
1.500 0.0133 0.02287 0.01148 0.0126 1.0000 1.0000
1.750 0.0257 0.02337 0.01197 0.0139 1.0000 1.0000
2.000 0.0385 0.02392 0.01250 0.0151 1.0000 1.0000
2.250 0.0515 0.02451 0.01309 0.0162 1.0000 1.0000
2.500 0.0646 0.02516 0.01374 0.0171 1.0000 1.0000
2.750 0.1054 0.02637 0.01506 0.0124 0.9887 1.0000
3.000 0.1596 0.02784 0.01667 0.0055 0.9708 1.0000
3.250 0.2085 0.02904 0.01803 -0.0002 0.9516 1.0000
3.500 0.2564 0.03010 0.01931 -0.0053 0.9310 1.0000
3.750 0.3049 0.03106 0.02049 -0.0103 0.9099 1.0000
4.000 0.3547 0.03183 0.02152 -0.0149 0.8871 1.0000
4.250 0.3985 0.03240 0.02242 -0.0182 0.8626 1.0000
4.500 0.4496 0.03271 0.02309 -0.0220 0.8363 1.0000
4.750 0.5146 0.03232 0.02320 -0.0269 0.8056 1.0000
5.000 0.6113 0.02981 0.02155 -0.0336 0.7646 1.0000
5.250 0.7048 0.02486 0.01743 -0.0349 0.7025 1.0000
5.500 0.7298 0.02244 0.01509 -0.0278 0.6179 1.0000
5.750 0.7313 0.02196 0.01408 -0.0190 0.4781 1.0000
6.000 0.7158 0.02436 0.01468 -0.0102 0.2840 1.0000
6.250 0.7204 0.02749 0.01673 -0.0061 0.1868 1.0000
6.500 0.7482 0.03014 0.01903 -0.0053 0.1459 1.0000
6.750 0.7782 0.03264 0.02153 -0.0049 0.1237 1.0000
7.000 0.8100 0.03567 0.02469 -0.0047 0.1136 1.0000
7.250 0.8334 0.03833 0.02751 -0.0037 0.1046 1.0000
7.500 0.8498 0.04126 0.03094 -0.0014 0.1003 1.0000
7.750 0.8644 0.04453 0.03472 0.0010 0.0993 1.0000
8.000 0.8748 0.04807 0.03873 0.0038 0.0994 1.0000
8.250 0.8812 0.05177 0.04287 0.0066 0.1001 1.0000
8.500 0.8841 0.05554 0.04703 0.0095 0.1010 1.0000
8.750 0.8822 0.05933 0.05118 0.0125 0.1012 1.0000
9.000 0.8803 0.06335 0.05547 0.0151 0.1020 1.0000
9.250 0.8801 0.06763 0.05992 0.0171 0.1029 1.0000
9.500 0.8343 0.07163 0.06454 0.0215 0.1105 1.0000
9.750 0.8175 0.07589 0.06890 0.0234 0.1134 1.0000
10.000 0.8127 0.08051 0.07354 0.0245 0.1157 1.0000
10.250 0.7466 0.08730 0.08044 0.0217 0.1258 1.0000
10.500 0.6208 0.08851 0.08190 0.0202 0.1258 1.0000
10.750 0.5913 0.09812 0.09144 0.0144 0.1358 1.0000
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Polar data table (+)
Polar graphs
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