HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL (tempest1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL (tempest1-il) Reynolds number: 200,000 Max Cl/Cd: 53.7 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tempest1-il-200000-n5.txt Download as CSV file: xf-tempest1-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7385 0.10509 0.10066 -0.0503 1.0000 0.0160
-16.250 -0.7757 0.09322 0.08852 -0.0574 1.0000 0.0159
-16.000 -0.7957 0.08581 0.08097 -0.0614 1.0000 0.0158
-15.750 -0.8160 0.07864 0.07360 -0.0655 1.0000 0.0158
-15.500 -0.8335 0.07247 0.06726 -0.0687 1.0000 0.0158
-15.250 -0.8491 0.06704 0.06165 -0.0712 1.0000 0.0159
-15.000 -0.8599 0.06271 0.05721 -0.0727 1.0000 0.0161
-14.750 -0.8702 0.05869 0.05305 -0.0738 1.0000 0.0161
-14.500 -0.8784 0.05517 0.04940 -0.0744 1.0000 0.0163
-14.250 -0.8853 0.05201 0.04614 -0.0745 1.0000 0.0165
-14.000 -0.8912 0.04912 0.04310 -0.0742 1.0000 0.0165
-13.750 -0.8959 0.04661 0.04051 -0.0735 1.0000 0.0169
-13.500 -0.9001 0.04423 0.03800 -0.0724 1.0000 0.0171
-13.250 -0.9031 0.04213 0.03578 -0.0710 1.0000 0.0174
-13.000 -0.9050 0.04022 0.03375 -0.0692 1.0000 0.0176
-12.750 -0.9064 0.03844 0.03185 -0.0672 1.0000 0.0179
-12.500 -0.9072 0.03681 0.03010 -0.0648 1.0000 0.0182
-12.250 -0.9075 0.03533 0.02848 -0.0622 1.0000 0.0185
-12.000 -0.9077 0.03395 0.02696 -0.0594 1.0000 0.0189
-11.750 -0.9068 0.03279 0.02566 -0.0563 1.0000 0.0195
-11.500 -0.9071 0.03167 0.02444 -0.0529 1.0000 0.0200
-11.250 -0.9090 0.03056 0.02328 -0.0491 1.0000 0.0202
-11.000 -0.9113 0.02975 0.02245 -0.0450 1.0000 0.0211
-10.750 -0.9135 0.02899 0.02163 -0.0406 1.0000 0.0214
-10.500 -0.9170 0.02830 0.02087 -0.0359 1.0000 0.0219
-10.250 -0.9215 0.02770 0.02021 -0.0307 1.0000 0.0226
-10.000 -0.9112 0.02688 0.01928 -0.0285 0.9982 0.0234
-9.750 -0.8880 0.02591 0.01814 -0.0287 0.9944 0.0246
-9.500 -0.8692 0.02484 0.01704 -0.0283 0.9898 0.0258
-9.250 -0.8460 0.02399 0.01611 -0.0284 0.9856 0.0275
-9.000 -0.8187 0.02321 0.01522 -0.0292 0.9826 0.0298
-8.750 -0.7997 0.02237 0.01434 -0.0283 0.9769 0.0324
-8.500 -0.7738 0.02164 0.01354 -0.0287 0.9728 0.0357
-8.250 -0.7458 0.02084 0.01272 -0.0296 0.9699 0.0406
-8.000 -0.7259 0.02022 0.01207 -0.0285 0.9636 0.0464
-7.750 -0.6996 0.01957 0.01142 -0.0288 0.9593 0.0554
-7.500 -0.6697 0.01893 0.01080 -0.0299 0.9564 0.0666
-7.250 -0.6472 0.01844 0.01033 -0.0293 0.9505 0.0784
-7.000 -0.6209 0.01795 0.00986 -0.0294 0.9456 0.0918
-6.750 -0.5898 0.01746 0.00936 -0.0305 0.9425 0.1049
-6.250 -0.5390 0.01662 0.00853 -0.0302 0.9321 0.1309
-5.750 -0.4769 0.01561 0.00762 -0.0324 0.9256 0.1661
-5.500 -0.4587 0.01524 0.00730 -0.0307 0.9177 0.1843
-5.250 -0.4316 0.01475 0.00690 -0.0309 0.9132 0.2103
-5.000 -0.4018 0.01421 0.00647 -0.0317 0.9099 0.2443
-4.750 -0.3869 0.01382 0.00621 -0.0292 0.9011 0.2792
-4.500 -0.3619 0.01327 0.00585 -0.0290 0.8965 0.3291
-4.250 -0.3444 0.01281 0.00559 -0.0271 0.8893 0.3807
-4.000 -0.3245 0.01235 0.00535 -0.0255 0.8828 0.4393
-3.750 -0.2996 0.01194 0.00511 -0.0250 0.8781 0.4911
-3.500 -0.2824 0.01171 0.00500 -0.0227 0.8696 0.5315
-3.250 -0.2549 0.01142 0.00480 -0.0226 0.8647 0.5703
-3.000 -0.2341 0.01125 0.00472 -0.0210 0.8570 0.6016
-2.750 -0.2072 0.01105 0.00459 -0.0207 0.8511 0.6328
-2.500 -0.1803 0.01090 0.00449 -0.0203 0.8449 0.6608
-2.250 -0.1547 0.01080 0.00445 -0.0197 0.8376 0.6865
-2.000 -0.1217 0.01067 0.00436 -0.0206 0.8326 0.7128
-1.750 -0.0983 0.01065 0.00440 -0.0194 0.8239 0.7398
-1.500 -0.0660 0.01061 0.00440 -0.0200 0.8181 0.7683
-1.250 -0.0371 0.01065 0.00448 -0.0200 0.8099 0.7888
-1.000 -0.0036 0.01067 0.00448 -0.0209 0.8034 0.8048
-0.750 0.0256 0.01073 0.00453 -0.0210 0.7951 0.8190
-0.500 0.0564 0.01075 0.00452 -0.0215 0.7877 0.8318
-0.250 0.0902 0.01084 0.00460 -0.0226 0.7790 0.8406
0.000 0.1227 0.01088 0.00459 -0.0234 0.7713 0.8497
0.250 0.1527 0.01096 0.00467 -0.0238 0.7616 0.8578
0.500 0.1845 0.01103 0.00469 -0.0245 0.7530 0.8652
0.750 0.2171 0.01112 0.00476 -0.0254 0.7430 0.8716
1.000 0.2437 0.01119 0.00480 -0.0250 0.7327 0.8796
1.250 0.2798 0.01129 0.00487 -0.0267 0.7225 0.8838
1.500 0.3046 0.01136 0.00492 -0.0259 0.7109 0.8918
2.000 0.3711 0.01160 0.00510 -0.0281 0.6858 0.9003
2.250 0.3914 0.01167 0.00515 -0.0264 0.6740 0.9090
2.500 0.4285 0.01181 0.00526 -0.0284 0.6613 0.9114
2.750 0.4625 0.01195 0.00538 -0.0297 0.6484 0.9146
3.000 0.4910 0.01208 0.00552 -0.0298 0.6352 0.9198
3.250 0.5158 0.01221 0.00562 -0.0292 0.6216 0.9258
3.500 0.5491 0.01238 0.00576 -0.0303 0.6045 0.9286
3.750 0.5786 0.01256 0.00590 -0.0307 0.5856 0.9327
4.000 0.5982 0.01271 0.00602 -0.0290 0.5685 0.9402
4.250 0.6312 0.01290 0.00620 -0.0302 0.5479 0.9428
4.500 0.6612 0.01311 0.00639 -0.0308 0.5270 0.9466
4.750 0.6832 0.01333 0.00657 -0.0297 0.5067 0.9531
5.000 0.7114 0.01356 0.00678 -0.0300 0.4821 0.9571
5.250 0.7397 0.01386 0.00701 -0.0304 0.4507 0.9610
5.500 0.7613 0.01420 0.00726 -0.0294 0.4191 0.9671
5.750 0.7851 0.01462 0.00754 -0.0290 0.3817 0.9717
6.000 0.8094 0.01512 0.00789 -0.0289 0.3417 0.9762
6.250 0.8281 0.01568 0.00829 -0.0276 0.3045 0.9823
6.500 0.8532 0.01628 0.00870 -0.0279 0.2639 0.9860
6.750 0.8764 0.01689 0.00916 -0.0278 0.2268 0.9904
7.000 0.8991 0.01752 0.00965 -0.0276 0.1935 0.9947
7.250 0.9237 0.01815 0.01015 -0.0279 0.1637 0.9985
7.500 0.9362 0.01869 0.01060 -0.0256 0.1443 1.0000
7.750 0.9363 0.01906 0.01094 -0.0206 0.1319 1.0000
8.000 0.9351 0.01941 0.01129 -0.0154 0.1212 1.0000
8.250 0.9344 0.01982 0.01167 -0.0104 0.1101 1.0000
8.500 0.9348 0.02028 0.01210 -0.0057 0.0995 1.0000
8.750 0.9362 0.02080 0.01258 -0.0013 0.0889 1.0000
9.000 0.9393 0.02135 0.01311 0.0028 0.0784 1.0000
9.250 0.9432 0.02195 0.01369 0.0065 0.0690 1.0000
9.500 0.9475 0.02261 0.01434 0.0101 0.0613 1.0000
9.750 0.9512 0.02338 0.01509 0.0136 0.0537 1.0000
10.000 0.9567 0.02413 0.01586 0.0167 0.0478 1.0000
10.250 0.9616 0.02499 0.01673 0.0198 0.0433 1.0000
10.500 0.9673 0.02586 0.01765 0.0226 0.0398 1.0000
10.750 0.9709 0.02693 0.01871 0.0254 0.0367 1.0000
11.000 0.9774 0.02789 0.01976 0.0279 0.0340 1.0000
11.250 0.9826 0.02899 0.02091 0.0302 0.0316 1.0000
11.500 0.9856 0.03029 0.02223 0.0326 0.0299 1.0000
11.750 0.9910 0.03151 0.02356 0.0347 0.0284 1.0000
12.000 0.9958 0.03284 0.02498 0.0367 0.0272 1.0000
12.250 0.9999 0.03427 0.02648 0.0385 0.0259 1.0000
12.500 1.0025 0.03587 0.02815 0.0402 0.0250 1.0000
12.750 1.0024 0.03777 0.03008 0.0419 0.0242 1.0000
13.000 1.0073 0.03936 0.03180 0.0432 0.0232 1.0000
13.250 1.0104 0.04115 0.03370 0.0444 0.0224 1.0000
13.500 1.0139 0.04297 0.03561 0.0454 0.0216 1.0000
13.750 1.0166 0.04492 0.03766 0.0463 0.0208 1.0000
14.000 1.0168 0.04717 0.03999 0.0471 0.0202 1.0000
14.250 1.0166 0.04957 0.04246 0.0477 0.0197 1.0000
14.500 1.0152 0.05214 0.04508 0.0482 0.0193 1.0000
14.750 1.0166 0.05455 0.04765 0.0486 0.0189 1.0000
15.000 1.0170 0.05715 0.05038 0.0488 0.0185 1.0000
15.250 1.0166 0.05991 0.05328 0.0488 0.0181 1.0000
15.500 1.0158 0.06278 0.05628 0.0487 0.0178 1.0000
15.750 1.0140 0.06587 0.05949 0.0484 0.0174 1.0000
16.000 1.0110 0.06924 0.06297 0.0476 0.0168 1.0000
16.250 1.0082 0.07265 0.06651 0.0468 0.0166 1.0000
16.500 1.0039 0.07632 0.07028 0.0459 0.0163 1.0000
16.750 0.9997 0.08011 0.07416 0.0447 0.0160 1.0000
17.000 0.9948 0.08408 0.07824 0.0435 0.0159 1.0000
17.250 0.9889 0.08826 0.08249 0.0420 0.0156 1.0000
17.500 0.9813 0.09285 0.08720 0.0403 0.0154 1.0000
17.750 0.9702 0.09834 0.09289 0.0379 0.0152 1.0000
18.000 0.9598 0.10382 0.09854 0.0354 0.0151 1.0000
18.250 0.9464 0.11006 0.10496 0.0323 0.0149 1.0000
18.500 0.9328 0.11647 0.11153 0.0291 0.0149 1.0000
18.750 0.9154 0.12393 0.11918 0.0252 0.0148 1.0000
19.000 0.8986 0.13154 0.12695 0.0211 0.0149 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL (tempest1-il)