HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Reynolds number: 500,000 Max Cl/Cd: 61.5 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tempest2-il-500000-n5.txt Download as CSV file: xf-tempest2-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7462 0.10759 0.10497 -0.0307 1.0000 0.0069
-15.250 -0.7908 0.09368 0.09094 -0.0377 1.0000 0.0068
-15.000 -0.8260 0.08183 0.07895 -0.0444 1.0000 0.0067
-14.750 -0.8541 0.07154 0.06849 -0.0509 1.0000 0.0067
-14.500 -0.8826 0.06220 0.05896 -0.0570 1.0000 0.0065
-14.250 -0.9007 0.05563 0.05221 -0.0611 1.0000 0.0065
-14.000 -0.9154 0.05040 0.04680 -0.0637 1.0000 0.0066
-13.750 -0.9307 0.04578 0.04199 -0.0652 1.0000 0.0066
-13.500 -0.9437 0.04198 0.03800 -0.0654 1.0000 0.0066
-13.250 -0.9519 0.03912 0.03497 -0.0646 1.0000 0.0067
-13.000 -0.9593 0.03659 0.03226 -0.0631 1.0000 0.0068
-12.750 -0.9633 0.03459 0.03008 -0.0611 1.0000 0.0069
-12.500 -0.9715 0.03240 0.02774 -0.0582 1.0000 0.0068
-12.250 -0.9724 0.03095 0.02612 -0.0553 1.0000 0.0070
-12.000 -0.9738 0.02960 0.02462 -0.0519 1.0000 0.0070
-11.750 -0.9744 0.02846 0.02335 -0.0483 1.0000 0.0071
-11.500 -0.9774 0.02735 0.02212 -0.0439 1.0000 0.0072
-11.250 -0.9849 0.02629 0.02093 -0.0384 1.0000 0.0074
-11.000 -0.9903 0.02547 0.02002 -0.0329 1.0000 0.0074
-10.750 -0.9904 0.02463 0.01909 -0.0284 1.0000 0.0076
-10.500 -0.9779 0.02371 0.01808 -0.0265 0.9991 0.0077
-10.250 -0.9533 0.02271 0.01698 -0.0269 0.9968 0.0080
-10.000 -0.9278 0.02178 0.01594 -0.0275 0.9943 0.0083
-9.750 -0.9041 0.02092 0.01498 -0.0275 0.9914 0.0087
-9.500 -0.8789 0.02014 0.01410 -0.0277 0.9885 0.0090
-9.250 -0.8525 0.01936 0.01319 -0.0281 0.9859 0.0095
-9.000 -0.8239 0.01872 0.01244 -0.0289 0.9839 0.0099
-8.750 -0.8008 0.01775 0.01138 -0.0287 0.9807 0.0102
-8.500 -0.7775 0.01697 0.01054 -0.0284 0.9766 0.0107
-8.250 -0.7501 0.01634 0.00986 -0.0288 0.9738 0.0113
-8.000 -0.7210 0.01575 0.00919 -0.0296 0.9716 0.0119
-7.750 -0.6905 0.01518 0.00856 -0.0306 0.9699 0.0127
-7.500 -0.6666 0.01473 0.00803 -0.0301 0.9650 0.0134
-7.250 -0.6397 0.01414 0.00741 -0.0303 0.9612 0.0149
-7.000 -0.6088 0.01364 0.00688 -0.0313 0.9585 0.0163
-6.750 -0.5765 0.01320 0.00637 -0.0326 0.9562 0.0178
-6.500 -0.5512 0.01275 0.00590 -0.0323 0.9505 0.0203
-6.250 -0.5229 0.01235 0.00548 -0.0326 0.9456 0.0235
-6.000 -0.4917 0.01192 0.00505 -0.0336 0.9420 0.0293
-5.750 -0.4666 0.01154 0.00469 -0.0333 0.9356 0.0386
-5.500 -0.4390 0.01114 0.00434 -0.0335 0.9299 0.0536
-5.250 -0.4106 0.01077 0.00404 -0.0339 0.9249 0.0717
-5.000 -0.3859 0.01048 0.00379 -0.0334 0.9174 0.0897
-4.750 -0.3574 0.01015 0.00352 -0.0338 0.9118 0.1091
-4.500 -0.3334 0.00990 0.00332 -0.0331 0.9037 0.1268
-4.250 -0.3062 0.00962 0.00308 -0.0331 0.8972 0.1486
-4.000 -0.2836 0.00930 0.00288 -0.0322 0.8887 0.1816
-3.750 -0.2595 0.00893 0.00266 -0.0317 0.8813 0.2271
-3.500 -0.2370 0.00860 0.00248 -0.0307 0.8726 0.2728
-3.250 -0.2146 0.00824 0.00229 -0.0298 0.8644 0.3277
-3.000 -0.1926 0.00790 0.00212 -0.0287 0.8556 0.3847
-2.750 -0.1709 0.00761 0.00199 -0.0275 0.8468 0.4387
-2.500 -0.1491 0.00733 0.00187 -0.0263 0.8383 0.4951
-2.250 -0.1270 0.00714 0.00178 -0.0251 0.8292 0.5353
-2.000 -0.1043 0.00697 0.00170 -0.0240 0.8205 0.5745
-1.750 -0.0813 0.00682 0.00163 -0.0230 0.8115 0.6082
-1.500 -0.0582 0.00670 0.00158 -0.0219 0.8021 0.6397
-1.250 -0.0349 0.00659 0.00153 -0.0209 0.7929 0.6706
-1.000 -0.0117 0.00649 0.00151 -0.0198 0.7829 0.7017
-0.750 0.0110 0.00638 0.00151 -0.0186 0.7728 0.7389
-0.500 0.0342 0.00631 0.00153 -0.0174 0.7626 0.7790
-0.250 0.0590 0.00628 0.00156 -0.0166 0.7516 0.8068
0.000 0.0849 0.00629 0.00159 -0.0160 0.7397 0.8265
0.250 0.1113 0.00631 0.00162 -0.0156 0.7275 0.8434
0.500 0.1378 0.00636 0.00165 -0.0152 0.7139 0.8567
0.750 0.1637 0.00642 0.00168 -0.0147 0.6985 0.8683
1.000 0.1908 0.00650 0.00172 -0.0145 0.6830 0.8780
1.250 0.2181 0.00658 0.00178 -0.0143 0.6676 0.8867
1.500 0.2436 0.00667 0.00182 -0.0138 0.6525 0.8958
1.750 0.2731 0.00678 0.00190 -0.0141 0.6380 0.9022
2.000 0.2982 0.00688 0.00197 -0.0136 0.6230 0.9105
2.250 0.3282 0.00702 0.00207 -0.0140 0.6061 0.9157
2.500 0.3543 0.00717 0.00216 -0.0137 0.5845 0.9225
2.750 0.3811 0.00735 0.00227 -0.0135 0.5610 0.9282
3.000 0.4106 0.00753 0.00240 -0.0140 0.5388 0.9327
3.250 0.4338 0.00770 0.00250 -0.0130 0.5172 0.9397
3.500 0.4645 0.00791 0.00265 -0.0137 0.4925 0.9429
3.750 0.4942 0.00816 0.00282 -0.0143 0.4620 0.9464
4.000 0.5194 0.00846 0.00300 -0.0139 0.4249 0.9515
4.250 0.5437 0.00884 0.00321 -0.0134 0.3803 0.9563
4.500 0.5729 0.00938 0.00350 -0.0142 0.3207 0.9587
4.750 0.5996 0.00998 0.00383 -0.0145 0.2594 0.9621
5.000 0.6223 0.01052 0.00415 -0.0138 0.2104 0.9675
5.250 0.6494 0.01101 0.00447 -0.0141 0.1699 0.9708
5.500 0.6788 0.01157 0.00484 -0.0150 0.1290 0.9730
5.750 0.7072 0.01204 0.00519 -0.0156 0.1011 0.9759
6.000 0.7330 0.01253 0.00555 -0.0157 0.0753 0.9796
6.250 0.7574 0.01298 0.00592 -0.0154 0.0565 0.9832
6.500 0.7867 0.01346 0.00634 -0.0162 0.0410 0.9850
6.750 0.8152 0.01394 0.00677 -0.0169 0.0307 0.9873
7.000 0.8430 0.01439 0.00721 -0.0174 0.0248 0.9900
7.250 0.8697 0.01484 0.00768 -0.0176 0.0211 0.9927
7.500 0.8968 0.01531 0.00818 -0.0180 0.0185 0.9950
7.750 0.9244 0.01585 0.00875 -0.0185 0.0163 0.9972
8.000 0.9527 0.01632 0.00928 -0.0191 0.0150 0.9992
8.250 0.9723 0.01678 0.00976 -0.0180 0.0136 1.0000
8.500 0.9813 0.01724 0.01025 -0.0146 0.0128 1.0000
8.750 0.9888 0.01776 0.01083 -0.0109 0.0123 1.0000
9.000 0.9977 0.01818 0.01132 -0.0075 0.0118 1.0000
9.250 1.0025 0.01860 0.01180 -0.0033 0.0113 1.0000
9.500 1.0080 0.01902 0.01227 0.0007 0.0109 1.0000
9.750 1.0140 0.01953 0.01284 0.0045 0.0105 1.0000
10.000 1.0214 0.02008 0.01345 0.0079 0.0103 1.0000
10.250 1.0297 0.02069 0.01410 0.0110 0.0098 1.0000
10.500 1.0364 0.02146 0.01492 0.0141 0.0093 1.0000
10.750 1.0418 0.02238 0.01592 0.0173 0.0090 1.0000
11.000 1.0527 0.02305 0.01667 0.0195 0.0086 1.0000
11.250 1.0610 0.02392 0.01763 0.0220 0.0084 1.0000
11.500 1.0691 0.02485 0.01866 0.0244 0.0081 1.0000
11.750 1.0775 0.02581 0.01970 0.0265 0.0078 1.0000
12.000 1.0842 0.02694 0.02093 0.0287 0.0077 1.0000
12.250 1.0917 0.02805 0.02213 0.0306 0.0074 1.0000
12.500 1.0978 0.02933 0.02349 0.0325 0.0072 1.0000
12.750 1.1044 0.03061 0.02485 0.0341 0.0070 1.0000
13.000 1.1065 0.03234 0.02672 0.0359 0.0070 1.0000
13.250 1.1119 0.03383 0.02829 0.0372 0.0068 1.0000
13.500 1.1135 0.03575 0.03032 0.0385 0.0067 1.0000
13.750 1.1134 0.03791 0.03260 0.0396 0.0066 1.0000
14.000 1.1077 0.04073 0.03554 0.0407 0.0064 1.0000
14.250 1.1087 0.04304 0.03798 0.0412 0.0063 1.0000
14.500 1.1046 0.04597 0.04105 0.0415 0.0063 1.0000
14.750 1.1030 0.04879 0.04401 0.0415 0.0062 1.0000
15.000 1.0980 0.05215 0.04753 0.0412 0.0061 1.0000
15.250 1.0945 0.05549 0.05101 0.0405 0.0061 1.0000
15.500 1.0866 0.05960 0.05528 0.0394 0.0060 1.0000
15.750 1.0778 0.06407 0.05992 0.0379 0.0059 1.0000
16.000 1.0680 0.06887 0.06488 0.0360 0.0058 1.0000
16.250 1.0513 0.07503 0.07121 0.0334 0.0058 1.0000
16.500 1.0458 0.07970 0.07599 0.0310 0.0058 1.0000
16.750 1.0281 0.08664 0.08310 0.0275 0.0057 1.0000
17.000 1.0076 0.09437 0.09099 0.0236 0.0058 1.0000
17.250 0.9867 0.10247 0.09924 0.0194 0.0059 1.0000
17.500 0.9625 0.11171 0.10864 0.0146 0.0057 1.0000
17.750 0.9408 0.12055 0.11760 0.0101 0.0059 1.0000
18.000 0.9155 0.13060 0.12779 0.0049 0.0059 1.0000
18.250 0.8861 0.14205 0.13936 -0.0009 0.0061 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il)