HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Reynolds number: 500,000 Max Cl/Cd: 71.9 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest2-il-500000.txt Download as CSV file: xf-tempest2-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 61% SEMISPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7316 0.06127 0.05845 -0.0610 1.0000 0.0131
-12.250 -0.7580 0.05513 0.05211 -0.0641 1.0000 0.0132
-12.000 -0.7826 0.05030 0.04712 -0.0647 1.0000 0.0131
-11.750 -0.8027 0.04674 0.04339 -0.0634 1.0000 0.0130
-11.500 -0.8240 0.04368 0.04013 -0.0605 1.0000 0.0131
-11.250 -0.8428 0.04142 0.03766 -0.0562 1.0000 0.0132
-11.000 -0.8634 0.03892 0.03501 -0.0508 1.0000 0.0130
-10.750 -0.8838 0.03738 0.03331 -0.0438 1.0000 0.0130
-10.500 -0.8986 0.03566 0.03140 -0.0376 1.0000 0.0131
-10.250 -0.9100 0.03372 0.02926 -0.0319 1.0000 0.0130
-10.000 -0.9159 0.03224 0.02758 -0.0267 1.0000 0.0132
-9.750 -0.9201 0.03064 0.02575 -0.0218 1.0000 0.0133
-9.500 -0.9197 0.02939 0.02431 -0.0174 1.0000 0.0134
-9.250 -0.9175 0.02814 0.02286 -0.0133 1.0000 0.0135
-9.000 -0.9012 0.02506 0.01941 -0.0124 0.9982 0.0139
-8.750 -0.8759 0.02296 0.01711 -0.0130 0.9960 0.0142
-8.500 -0.8469 0.02166 0.01574 -0.0141 0.9940 0.0148
-8.250 -0.8193 0.02078 0.01478 -0.0148 0.9910 0.0156
-8.000 -0.7896 0.01992 0.01384 -0.0157 0.9882 0.0165
-7.750 -0.7589 0.01890 0.01268 -0.0168 0.9858 0.0174
-7.500 -0.7259 0.01814 0.01181 -0.0182 0.9840 0.0181
-7.250 -0.7018 0.01661 0.01018 -0.0181 0.9805 0.0193
-7.000 -0.6751 0.01577 0.00929 -0.0183 0.9763 0.0204
-6.750 -0.6431 0.01514 0.00862 -0.0196 0.9735 0.0220
-6.500 -0.6082 0.01469 0.00810 -0.0213 0.9715 0.0241
-6.250 -0.5762 0.01370 0.00708 -0.0227 0.9698 0.0285
-6.000 -0.5523 0.01328 0.00660 -0.0220 0.9638 0.0317
-5.750 -0.5224 0.01255 0.00590 -0.0227 0.9605 0.0433
-5.500 -0.4900 0.01184 0.00539 -0.0240 0.9583 0.0765
-5.250 -0.4547 0.01136 0.00503 -0.0260 0.9568 0.1053
-5.000 -0.4178 0.01095 0.00470 -0.0282 0.9556 0.1308
-4.750 -0.3951 0.01059 0.00443 -0.0273 0.9489 0.1541
-4.500 -0.3640 0.01012 0.00411 -0.0283 0.9455 0.1910
-4.250 -0.3325 0.00954 0.00377 -0.0295 0.9427 0.2506
-4.000 -0.3102 0.00891 0.00349 -0.0287 0.9369 0.3342
-3.750 -0.2899 0.00822 0.00322 -0.0274 0.9305 0.4394
-3.500 -0.2639 0.00769 0.00299 -0.0271 0.9265 0.5268
-3.250 -0.2459 0.00740 0.00287 -0.0250 0.9179 0.5781
-3.000 -0.2193 0.00710 0.00270 -0.0246 0.9129 0.6260
-2.750 -0.1975 0.00692 0.00261 -0.0232 0.9050 0.6620
-2.500 -0.1715 0.00671 0.00250 -0.0226 0.8989 0.6991
-2.250 -0.1479 0.00658 0.00244 -0.0216 0.8914 0.7305
-2.000 -0.1212 0.00647 0.00236 -0.0211 0.8846 0.7581
-1.750 -0.0960 0.00639 0.00233 -0.0204 0.8768 0.7824
-1.500 -0.0683 0.00633 0.00228 -0.0201 0.8696 0.8036
-1.250 -0.0431 0.00631 0.00226 -0.0193 0.8609 0.8229
-1.000 -0.0137 0.00629 0.00224 -0.0195 0.8536 0.8396
-0.750 0.0126 0.00630 0.00228 -0.0189 0.8441 0.8575
-0.500 0.0412 0.00636 0.00234 -0.0187 0.8357 0.8762
-0.250 0.0700 0.00643 0.00240 -0.0186 0.8262 0.8897
0.000 0.0982 0.00651 0.00247 -0.0185 0.8159 0.9006
0.250 0.1245 0.00660 0.00252 -0.0179 0.8057 0.9114
0.500 0.1599 0.00672 0.00260 -0.0193 0.7949 0.9164
0.750 0.1844 0.00681 0.00265 -0.0184 0.7820 0.9251
1.000 0.2194 0.00692 0.00274 -0.0198 0.7694 0.9287
1.250 0.2541 0.00705 0.00284 -0.0212 0.7567 0.9322
1.500 0.2818 0.00716 0.00291 -0.0210 0.7437 0.9385
1.750 0.3146 0.00728 0.00300 -0.0221 0.7307 0.9421
2.000 0.3526 0.00741 0.00309 -0.0242 0.7159 0.9438
2.250 0.3890 0.00756 0.00319 -0.0261 0.6979 0.9458
2.500 0.4222 0.00771 0.00329 -0.0272 0.6786 0.9490
2.750 0.4456 0.00784 0.00337 -0.0262 0.6615 0.9555
3.000 0.4826 0.00798 0.00348 -0.0283 0.6422 0.9570
3.250 0.5180 0.00814 0.00360 -0.0300 0.6218 0.9590
3.500 0.5513 0.00832 0.00373 -0.0312 0.5996 0.9618
3.750 0.5799 0.00851 0.00386 -0.0315 0.5761 0.9663
4.000 0.6078 0.00870 0.00399 -0.0316 0.5487 0.9704
4.250 0.6411 0.00898 0.00413 -0.0330 0.5048 0.9727
4.500 0.6715 0.00934 0.00430 -0.0339 0.4500 0.9759
4.750 0.6959 0.00985 0.00453 -0.0336 0.3847 0.9809
5.000 0.7233 0.01046 0.00482 -0.0340 0.3124 0.9843
5.250 0.7535 0.01110 0.00513 -0.0353 0.2415 0.9871
5.500 0.7822 0.01174 0.00547 -0.0361 0.1803 0.9906
5.750 0.8099 0.01234 0.00586 -0.0367 0.1345 0.9941
6.000 0.8412 0.01290 0.00621 -0.0382 0.0941 0.9965
6.250 0.8704 0.01362 0.00669 -0.0392 0.0541 0.9993
6.500 0.8867 0.01425 0.00723 -0.0373 0.0381 1.0000
6.750 0.8994 0.01466 0.00765 -0.0346 0.0326 1.0000
7.000 0.9091 0.01524 0.00827 -0.0312 0.0284 1.0000
7.250 0.9211 0.01563 0.00871 -0.0283 0.0260 1.0000
7.500 0.9297 0.01619 0.00928 -0.0248 0.0238 1.0000
7.750 0.9353 0.01687 0.01002 -0.0208 0.0219 1.0000
8.000 0.9447 0.01732 0.01054 -0.0174 0.0210 1.0000
8.250 0.9532 0.01779 0.01106 -0.0138 0.0197 1.0000
8.500 0.9600 0.01833 0.01164 -0.0100 0.0189 1.0000
8.750 0.9649 0.01891 0.01227 -0.0059 0.0182 1.0000
9.000 0.9616 0.01968 0.01308 -0.0002 0.0174 1.0000
9.250 0.9558 0.02100 0.01448 0.0056 0.0167 1.0000
9.500 0.9661 0.02138 0.01493 0.0086 0.0161 1.0000
9.750 0.9746 0.02205 0.01568 0.0117 0.0156 1.0000
10.000 0.9828 0.02297 0.01668 0.0148 0.0153 1.0000
10.250 0.9927 0.02367 0.01744 0.0174 0.0146 1.0000
10.500 1.0018 0.02459 0.01843 0.0200 0.0140 1.0000
10.750 1.0112 0.02559 0.01951 0.0224 0.0137 1.0000
11.000 1.0192 0.02667 0.02064 0.0248 0.0131 1.0000
11.250 1.0271 0.02823 0.02229 0.0271 0.0128 1.0000
11.500 1.0335 0.03139 0.02565 0.0292 0.0123 1.0000
11.750 1.0384 0.03231 0.02673 0.0318 0.0121 1.0000
12.000 1.0430 0.03389 0.02848 0.0340 0.0120 1.0000
12.250 1.0450 0.03572 0.03050 0.0364 0.0118 1.0000
12.500 1.0449 0.03782 0.03279 0.0386 0.0117 1.0000
12.750 1.0417 0.04015 0.03533 0.0407 0.0115 1.0000
13.000 1.0385 0.04248 0.03783 0.0424 0.0114 1.0000
13.250 1.0287 0.04565 0.04123 0.0440 0.0113 1.0000
13.500 1.0252 0.04795 0.04367 0.0448 0.0109 1.0000
13.750 1.0151 0.05135 0.04725 0.0454 0.0108 1.0000
14.000 1.0029 0.05518 0.05127 0.0453 0.0107 1.0000
14.250 0.9820 0.06050 0.05683 0.0444 0.0107 1.0000
14.500 0.9600 0.06645 0.06299 0.0426 0.0110 1.0000
14.750 0.9512 0.07073 0.06740 0.0406 0.0107 1.0000
15.000 0.9085 0.08133 0.07828 0.0355 0.0113 1.0000
15.250 0.8970 0.08726 0.08433 0.0319 0.0110 1.0000
15.500 0.8676 0.09734 0.09458 0.0258 0.0113 1.0000
15.750 0.8288 0.11073 0.10814 0.0178 0.0116 1.0000
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