HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Reynolds number: 100,000 Max Cl/Cd: 46.88 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tempest3-il-100000-n5.txt Download as CSV file: xf-tempest3-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4235 0.12117 0.11615 -0.0235 1.0000 0.0260
-12.000 -0.4304 0.11568 0.11069 -0.0257 1.0000 0.0248
-11.500 -0.5361 0.11178 0.10647 -0.0253 1.0000 0.0230
-11.250 -0.5377 0.10714 0.10186 -0.0268 1.0000 0.0227
-11.000 -0.5396 0.10258 0.09735 -0.0285 1.0000 0.0224
-10.750 -0.5431 0.09767 0.09248 -0.0305 1.0000 0.0223
-10.500 -0.5485 0.09232 0.08719 -0.0329 1.0000 0.0221
-10.250 -0.5568 0.08614 0.08107 -0.0361 1.0000 0.0220
-10.000 -0.5648 0.08001 0.07499 -0.0397 1.0000 0.0216
-9.750 -0.5798 0.07231 0.06730 -0.0454 1.0000 0.0213
-9.500 -0.5991 0.06683 0.06177 -0.0479 1.0000 0.0210
-9.250 -0.6204 0.06274 0.05762 -0.0472 1.0000 0.0208
-9.000 -0.6401 0.05959 0.05443 -0.0444 1.0000 0.0206
-8.750 -0.6569 0.05594 0.05063 -0.0415 1.0000 0.0205
-8.500 -0.6699 0.05236 0.04684 -0.0383 1.0000 0.0204
-8.250 -0.6790 0.04893 0.04315 -0.0349 1.0000 0.0203
-8.000 -0.6856 0.04549 0.03939 -0.0312 1.0000 0.0206
-7.750 -0.6878 0.04243 0.03593 -0.0276 1.0000 0.0209
-7.500 -0.6868 0.03965 0.03271 -0.0240 1.0000 0.0220
-7.250 -0.6825 0.03710 0.02970 -0.0205 1.0000 0.0226
-7.000 -0.6749 0.03496 0.02711 -0.0174 1.0000 0.0232
-6.750 -0.6659 0.03234 0.02413 -0.0144 1.0000 0.0235
-6.500 -0.6542 0.02983 0.02132 -0.0119 1.0000 0.0241
-6.250 -0.6400 0.02791 0.01918 -0.0097 1.0000 0.0249
-6.000 -0.6242 0.02634 0.01742 -0.0077 1.0000 0.0258
-5.750 -0.6077 0.02496 0.01587 -0.0057 1.0000 0.0272
-5.500 -0.5908 0.02387 0.01462 -0.0038 1.0000 0.0297
-5.250 -0.5733 0.02293 0.01344 -0.0019 1.0000 0.0323
-5.000 -0.5579 0.02168 0.01213 0.0003 1.0000 0.0348
-4.750 -0.5423 0.02076 0.01115 0.0024 1.0000 0.0378
-4.500 -0.5200 0.01996 0.01021 0.0032 0.9982 0.0431
-4.250 -0.4887 0.01908 0.00929 0.0021 0.9934 0.0562
-4.000 -0.4593 0.01811 0.00852 0.0013 0.9878 0.0863
-3.750 -0.4278 0.01733 0.00797 -0.0001 0.9829 0.1464
-3.500 -0.4005 0.01649 0.00753 -0.0007 0.9767 0.2279
-3.250 -0.3748 0.01533 0.00722 -0.0011 0.9711 0.3962
-3.000 -0.3507 0.01448 0.00714 -0.0004 0.9651 0.5783
-2.750 -0.3188 0.01414 0.00718 -0.0005 0.9603 0.7056
-2.500 -0.2769 0.01419 0.00733 -0.0024 0.9575 0.7926
-2.250 -0.2303 0.01439 0.00746 -0.0056 0.9554 0.8463
-2.000 -0.1880 0.01459 0.00751 -0.0080 0.9511 0.8814
-1.750 -0.1407 0.01488 0.00767 -0.0114 0.9480 0.9139
-1.500 -0.0823 0.01527 0.00792 -0.0170 0.9475 0.9417
-1.250 -0.0294 0.01540 0.00789 -0.0221 0.9451 0.9555
-1.000 0.0226 0.01537 0.00776 -0.0273 0.9424 0.9633
-0.750 0.0673 0.01532 0.00762 -0.0311 0.9369 0.9715
-0.500 0.1140 0.01521 0.00746 -0.0354 0.9317 0.9781
-0.250 0.1618 0.01508 0.00729 -0.0398 0.9274 0.9837
0.000 0.2049 0.01492 0.00711 -0.0433 0.9195 0.9896
0.250 0.2512 0.01475 0.00694 -0.0475 0.9139 0.9944
0.500 0.2944 0.01456 0.00678 -0.0510 0.9050 0.9998
0.750 0.3269 0.01441 0.00666 -0.0522 0.8940 1.0000
1.000 0.3585 0.01426 0.00653 -0.0531 0.8824 1.0000
1.250 0.3884 0.01412 0.00642 -0.0536 0.8695 1.0000
1.500 0.4160 0.01400 0.00634 -0.0536 0.8550 1.0000
1.750 0.4419 0.01390 0.00630 -0.0531 0.8388 1.0000
2.000 0.4672 0.01380 0.00625 -0.0525 0.8214 1.0000
2.250 0.4928 0.01372 0.00620 -0.0518 0.8037 1.0000
2.500 0.5172 0.01366 0.00619 -0.0510 0.7854 1.0000
2.750 0.5395 0.01366 0.00627 -0.0497 0.7654 1.0000
3.000 0.5630 0.01363 0.00628 -0.0485 0.7443 1.0000
3.250 0.5843 0.01364 0.00632 -0.0469 0.7180 1.0000
3.500 0.6052 0.01369 0.00637 -0.0451 0.6885 1.0000
3.750 0.6251 0.01378 0.00651 -0.0432 0.6570 1.0000
4.000 0.6447 0.01392 0.00663 -0.0412 0.6214 1.0000
4.250 0.6629 0.01414 0.00676 -0.0389 0.5764 1.0000
4.500 0.6780 0.01449 0.00691 -0.0361 0.5109 1.0000
4.750 0.6888 0.01512 0.00711 -0.0327 0.4137 1.0000
5.000 0.6968 0.01609 0.00749 -0.0291 0.3072 1.0000
5.250 0.7054 0.01720 0.00812 -0.0259 0.2106 1.0000
5.500 0.7144 0.01842 0.00883 -0.0230 0.1265 1.0000
5.750 0.7249 0.01959 0.00968 -0.0201 0.0784 1.0000
6.000 0.7370 0.02063 0.01061 -0.0174 0.0566 1.0000
6.250 0.7492 0.02166 0.01167 -0.0146 0.0472 1.0000
6.500 0.7603 0.02276 0.01276 -0.0118 0.0405 1.0000
6.750 0.7742 0.02368 0.01382 -0.0093 0.0360 1.0000
7.000 0.7867 0.02479 0.01507 -0.0067 0.0331 1.0000
7.250 0.7992 0.02608 0.01640 -0.0042 0.0310 1.0000
7.500 0.8136 0.02765 0.01804 -0.0021 0.0285 1.0000
7.750 0.8310 0.02891 0.01950 -0.0003 0.0261 1.0000
8.000 0.8487 0.03052 0.02128 0.0013 0.0244 1.0000
8.250 0.8661 0.03235 0.02329 0.0029 0.0232 1.0000
8.500 0.8825 0.03436 0.02551 0.0045 0.0224 1.0000
8.750 0.8965 0.03670 0.02806 0.0063 0.0216 1.0000
9.000 0.9067 0.03977 0.03142 0.0083 0.0208 1.0000
9.250 0.9127 0.04210 0.03413 0.0111 0.0201 1.0000
9.500 0.9150 0.04432 0.03680 0.0145 0.0191 1.0000
9.750 0.9139 0.04698 0.03982 0.0178 0.0186 1.0000
10.000 0.9083 0.04973 0.04290 0.0213 0.0182 1.0000
10.250 0.8964 0.05251 0.04596 0.0253 0.0180 1.0000
10.500 0.8825 0.05542 0.04912 0.0288 0.0180 1.0000
10.750 0.8670 0.05859 0.05252 0.0313 0.0181 1.0000
11.000 0.8490 0.06225 0.05639 0.0327 0.0181 1.0000
11.250 0.8298 0.06640 0.06074 0.0329 0.0182 1.0000
11.500 0.8093 0.07132 0.06583 0.0317 0.0183 1.0000
11.750 0.7876 0.07722 0.07187 0.0289 0.0184 1.0000
12.000 0.7670 0.08406 0.07883 0.0246 0.0187 1.0000
12.250 0.7453 0.09261 0.08746 0.0189 0.0189 1.0000
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Polar data table (+)
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