HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.63 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest3-il-1000000.txt Download as CSV file: xf-tempest3-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6601 0.05600 0.05432 -0.0512 1.0000 0.0066
-10.250 -0.6958 0.04915 0.04729 -0.0536 1.0000 0.0065
-10.000 -0.7225 0.04525 0.04323 -0.0506 1.0000 0.0066
-9.750 -0.7505 0.04299 0.04086 -0.0443 1.0000 0.0064
-9.500 -0.7824 0.03861 0.03621 -0.0376 1.0000 0.0064
-9.250 -0.8079 0.03486 0.03217 -0.0307 1.0000 0.0063
-9.000 -0.8255 0.03158 0.02860 -0.0243 1.0000 0.0062
-8.750 -0.8171 0.02721 0.02374 -0.0230 0.9980 0.0064
-8.500 -0.7891 0.02607 0.02239 -0.0239 0.9962 0.0068
-8.250 -0.7600 0.02514 0.02126 -0.0250 0.9946 0.0070
-8.000 -0.7497 0.01979 0.01527 -0.0233 0.9910 0.0072
-7.750 -0.7253 0.01772 0.01294 -0.0234 0.9885 0.0074
-7.500 -0.6980 0.01612 0.01119 -0.0239 0.9864 0.0077
-7.250 -0.6673 0.01519 0.01016 -0.0250 0.9848 0.0080
-7.000 -0.6346 0.01461 0.00952 -0.0265 0.9836 0.0085
-6.750 -0.6017 0.01383 0.00865 -0.0279 0.9825 0.0091
-6.500 -0.5765 0.01311 0.00786 -0.0275 0.9782 0.0096
-6.250 -0.5466 0.01243 0.00710 -0.0282 0.9755 0.0101
-6.000 -0.5140 0.01200 0.00662 -0.0294 0.9736 0.0105
-5.750 -0.4846 0.01076 0.00522 -0.0301 0.9717 0.0116
-5.500 -0.4515 0.01018 0.00459 -0.0314 0.9701 0.0127
-5.250 -0.4214 0.00979 0.00417 -0.0321 0.9671 0.0139
-5.000 -0.3936 0.00949 0.00384 -0.0322 0.9621 0.0155
-4.750 -0.3643 0.00898 0.00327 -0.0326 0.9582 0.0194
-4.500 -0.3323 0.00862 0.00288 -0.0336 0.9551 0.0260
-4.250 -0.3100 0.00817 0.00258 -0.0325 0.9472 0.0538
-4.000 -0.2820 0.00778 0.00233 -0.0327 0.9421 0.0913
-3.750 -0.2575 0.00751 0.00216 -0.0321 0.9345 0.1205
-3.500 -0.2306 0.00723 0.00196 -0.0320 0.9280 0.1535
-3.250 -0.2072 0.00691 0.00180 -0.0312 0.9194 0.1987
-3.000 -0.1840 0.00645 0.00162 -0.0305 0.9117 0.2822
-2.750 -0.1633 0.00595 0.00145 -0.0292 0.9023 0.3833
-2.500 -0.1447 0.00537 0.00131 -0.0275 0.8930 0.5135
-2.250 -0.1223 0.00508 0.00121 -0.0263 0.8843 0.5861
-2.000 -0.0999 0.00486 0.00114 -0.0251 0.8746 0.6394
-1.750 -0.0774 0.00466 0.00108 -0.0239 0.8651 0.6912
-1.500 -0.0538 0.00453 0.00103 -0.0229 0.8558 0.7325
-1.250 -0.0300 0.00443 0.00100 -0.0219 0.8455 0.7687
-1.000 -0.0057 0.00435 0.00099 -0.0211 0.8352 0.8006
-0.750 0.0194 0.00431 0.00098 -0.0203 0.8249 0.8258
-0.500 0.0449 0.00430 0.00098 -0.0197 0.8140 0.8475
-0.250 0.0707 0.00430 0.00098 -0.0192 0.8020 0.8659
0.000 0.0964 0.00431 0.00100 -0.0186 0.7890 0.8845
0.250 0.1232 0.00435 0.00106 -0.0181 0.7753 0.9059
0.500 0.1501 0.00442 0.00112 -0.0177 0.7616 0.9218
0.750 0.1782 0.00451 0.00117 -0.0177 0.7482 0.9319
1.000 0.2041 0.00459 0.00122 -0.0172 0.7344 0.9416
1.250 0.2352 0.00470 0.00130 -0.0178 0.7196 0.9467
1.500 0.2608 0.00481 0.00136 -0.0172 0.7039 0.9539
1.750 0.2925 0.00494 0.00143 -0.0181 0.6826 0.9572
2.000 0.3248 0.00510 0.00151 -0.0191 0.6585 0.9601
2.250 0.3563 0.00525 0.00161 -0.0200 0.6374 0.9633
2.500 0.3806 0.00540 0.00170 -0.0192 0.6174 0.9688
2.750 0.4161 0.00557 0.00179 -0.0210 0.5926 0.9699
3.000 0.4506 0.00576 0.00190 -0.0226 0.5638 0.9710
3.250 0.4831 0.00605 0.00203 -0.0239 0.5175 0.9726
3.500 0.5144 0.00638 0.00218 -0.0248 0.4632 0.9747
3.750 0.5416 0.00693 0.00238 -0.0251 0.3770 0.9779
4.000 0.5637 0.00750 0.00263 -0.0243 0.2980 0.9824
4.250 0.5950 0.00809 0.00289 -0.0256 0.2202 0.9838
4.500 0.6261 0.00867 0.00317 -0.0268 0.1512 0.9854
4.750 0.6566 0.00926 0.00349 -0.0279 0.0935 0.9875
5.000 0.6861 0.00987 0.00385 -0.0288 0.0448 0.9901
5.250 0.7156 0.01035 0.00424 -0.0295 0.0251 0.9927
5.500 0.7461 0.01075 0.00465 -0.0303 0.0188 0.9946
5.750 0.7781 0.01117 0.00507 -0.0315 0.0151 0.9960
6.000 0.8090 0.01164 0.00561 -0.0325 0.0133 0.9976
6.250 0.8402 0.01202 0.00604 -0.0335 0.0120 0.9991
6.500 0.8675 0.01240 0.00644 -0.0338 0.0108 1.0000
6.750 0.8821 0.01294 0.00703 -0.0313 0.0100 1.0000
7.000 0.8886 0.01408 0.00833 -0.0272 0.0091 1.0000
7.250 0.9057 0.01439 0.00867 -0.0253 0.0089 1.0000
7.500 0.9218 0.01477 0.00910 -0.0231 0.0085 1.0000
7.750 0.9378 0.01516 0.00953 -0.0210 0.0079 1.0000
8.000 0.9527 0.01565 0.01008 -0.0186 0.0074 1.0000
8.250 0.9668 0.01620 0.01068 -0.0161 0.0071 1.0000
8.500 0.9802 0.01683 0.01137 -0.0135 0.0069 1.0000
8.750 0.9924 0.01758 0.01218 -0.0108 0.0066 1.0000
9.000 1.0021 0.01864 0.01333 -0.0077 0.0063 1.0000
9.250 1.0081 0.02040 0.01526 -0.0041 0.0060 1.0000
9.500 1.0140 0.02262 0.01771 -0.0006 0.0059 1.0000
9.750 1.0277 0.02329 0.01848 0.0017 0.0058 1.0000
10.000 1.0403 0.02409 0.01940 0.0040 0.0056 1.0000
10.250 1.0483 0.02560 0.02108 0.0070 0.0055 1.0000
10.500 1.0573 0.02650 0.02213 0.0099 0.0053 1.0000
10.750 1.0599 0.02780 0.02359 0.0137 0.0051 1.0000
11.000 1.0568 0.02983 0.02583 0.0179 0.0051 1.0000
11.250 1.0585 0.03113 0.02727 0.0213 0.0048 1.0000
11.500 1.0509 0.03356 0.02995 0.0251 0.0047 1.0000
11.750 1.0380 0.03656 0.03320 0.0289 0.0047 1.0000
12.000 1.0196 0.04022 0.03713 0.0320 0.0047 1.0000
12.250 0.9933 0.04502 0.04222 0.0342 0.0048 1.0000
12.500 0.9668 0.05033 0.04778 0.0346 0.0048 1.0000
12.750 0.9486 0.05518 0.05280 0.0336 0.0049 1.0000
13.000 0.9192 0.06255 0.06038 0.0303 0.0050 1.0000
13.250 0.8983 0.06963 0.06761 0.0260 0.0050 1.0000
13.500 0.8712 0.07928 0.07742 0.0194 0.0051 1.0000
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Polar data table (+)
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