SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7037-092-88 (sd7037-il) Reynolds number: 500,000 Max Cl/Cd: 99.29 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7037-il-500000.txt Download as CSV file: xf-sd7037-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SD7037-092-88
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3023 0.08198 0.07986 -0.0377 1.0000 0.0211
-9.000 -0.3055 0.07804 0.07595 -0.0384 1.0000 0.0212
-8.750 -0.3163 0.07293 0.07088 -0.0381 1.0000 0.0215
-8.500 -0.3211 0.07030 0.06829 -0.0367 1.0000 0.0217
-8.250 -0.3294 0.06810 0.06613 -0.0347 1.0000 0.0219
-8.000 -0.3406 0.06613 0.06420 -0.0324 1.0000 0.0221
-7.750 -0.3399 0.06267 0.06076 -0.0337 0.9986 0.0224
-7.500 -0.3309 0.05784 0.05594 -0.0382 0.9956 0.0228
-7.250 -0.3254 0.05223 0.05033 -0.0446 0.9904 0.0231
-7.000 -0.3121 0.04451 0.04257 -0.0565 0.9861 0.0237
-6.750 -0.2982 0.03622 0.03415 -0.0672 0.9816 0.0245
-6.500 -0.2789 0.02661 0.02394 -0.0776 0.9763 0.0272
-6.250 -0.2634 0.01818 0.01517 -0.0830 0.9735 0.0283
-6.000 -0.2382 0.01601 0.01297 -0.0846 0.9698 0.0292
-5.750 -0.2142 0.01382 0.01062 -0.0858 0.9646 0.0307
-5.500 -0.2188 0.02082 0.01619 -0.0860 0.9658 0.0204
-5.250 -0.1884 0.01699 0.01180 -0.0870 0.9625 0.0183
-5.000 -0.1552 0.01525 0.00978 -0.0880 0.9599 0.0182
-4.750 -0.1272 0.01436 0.00878 -0.0880 0.9550 0.0188
-4.500 -0.0997 0.01327 0.00754 -0.0877 0.9497 0.0189
-4.250 -0.0703 0.01227 0.00643 -0.0878 0.9456 0.0189
-4.000 -0.0454 0.01157 0.00565 -0.0869 0.9390 0.0193
-3.750 -0.0189 0.01095 0.00497 -0.0864 0.9330 0.0201
-3.500 0.0073 0.01047 0.00442 -0.0857 0.9271 0.0209
-3.250 0.0324 0.00986 0.00376 -0.0850 0.9195 0.0226
-3.000 0.0589 0.00950 0.00336 -0.0844 0.9133 0.0252
-2.750 0.0847 0.00913 0.00298 -0.0837 0.9048 0.0319
-2.500 0.1105 0.00847 0.00258 -0.0832 0.8975 0.0997
-2.250 0.1363 0.00806 0.00239 -0.0827 0.8884 0.1647
-2.000 0.1623 0.00765 0.00223 -0.0824 0.8794 0.2480
-1.750 0.1881 0.00717 0.00208 -0.0820 0.8703 0.3616
-1.500 0.2132 0.00667 0.00201 -0.0815 0.8588 0.4970
-1.250 0.2383 0.00629 0.00195 -0.0808 0.8471 0.6132
-1.000 0.2632 0.00601 0.00191 -0.0799 0.8347 0.7049
-0.750 0.2871 0.00578 0.00188 -0.0786 0.8212 0.7886
-0.500 0.3094 0.00561 0.00185 -0.0768 0.8065 0.8607
-0.250 0.3326 0.00552 0.00180 -0.0752 0.7905 0.9198
0.000 0.3702 0.00548 0.00169 -0.0769 0.7733 0.9736
0.250 0.4083 0.00551 0.00160 -0.0790 0.7547 1.0000
0.500 0.4340 0.00562 0.00156 -0.0784 0.7353 1.0000
0.750 0.4600 0.00573 0.00155 -0.0779 0.7151 1.0000
1.000 0.4860 0.00586 0.00156 -0.0775 0.6948 1.0000
1.250 0.5122 0.00600 0.00158 -0.0770 0.6745 1.0000
1.500 0.5384 0.00614 0.00161 -0.0766 0.6535 1.0000
1.750 0.5645 0.00631 0.00166 -0.0762 0.6332 1.0000
2.000 0.5909 0.00646 0.00171 -0.0759 0.6122 1.0000
2.250 0.6170 0.00663 0.00179 -0.0755 0.5912 1.0000
2.500 0.6432 0.00681 0.00187 -0.0751 0.5703 1.0000
2.750 0.6695 0.00699 0.00196 -0.0748 0.5490 1.0000
3.000 0.6955 0.00720 0.00206 -0.0744 0.5280 1.0000
3.250 0.7217 0.00739 0.00219 -0.0741 0.5066 1.0000
3.500 0.7475 0.00762 0.00231 -0.0737 0.4851 1.0000
3.750 0.7736 0.00783 0.00245 -0.0734 0.4637 1.0000
4.000 0.7993 0.00807 0.00260 -0.0730 0.4416 1.0000
4.250 0.8251 0.00831 0.00278 -0.0726 0.4199 1.0000
4.500 0.8506 0.00858 0.00296 -0.0722 0.3976 1.0000
4.750 0.8761 0.00885 0.00315 -0.0719 0.3758 1.0000
5.000 0.9014 0.00914 0.00337 -0.0715 0.3536 1.0000
5.250 0.9266 0.00944 0.00360 -0.0711 0.3327 1.0000
5.500 0.9516 0.00976 0.00384 -0.0707 0.3106 1.0000
5.750 0.9765 0.01009 0.00410 -0.0702 0.2900 1.0000
6.000 1.0010 0.01046 0.00439 -0.0697 0.2666 1.0000
6.250 1.0253 0.01084 0.00469 -0.0692 0.2452 1.0000
6.500 1.0496 0.01122 0.00500 -0.0688 0.2249 1.0000
6.750 1.0734 0.01164 0.00535 -0.0682 0.2054 1.0000
7.000 1.0972 0.01205 0.00570 -0.0677 0.1850 1.0000
7.250 1.1204 0.01252 0.00608 -0.0670 0.1657 1.0000
7.500 1.1436 0.01298 0.00648 -0.0664 0.1488 1.0000
7.750 1.1666 0.01345 0.00690 -0.0658 0.1310 1.0000
8.000 1.1892 0.01394 0.00735 -0.0651 0.1154 1.0000
8.250 1.2109 0.01451 0.00783 -0.0643 0.0988 1.0000
8.500 1.2325 0.01507 0.00834 -0.0635 0.0849 1.0000
8.750 1.2536 0.01565 0.00890 -0.0626 0.0715 1.0000
9.000 1.2741 0.01628 0.00948 -0.0616 0.0583 1.0000
9.250 1.2921 0.01713 0.01022 -0.0604 0.0412 1.0000
9.500 1.3063 0.01830 0.01127 -0.0585 0.0229 1.0000
9.750 1.3222 0.01927 0.01224 -0.0568 0.0174 1.0000
10.000 1.3374 0.02023 0.01325 -0.0551 0.0152 1.0000
10.250 1.3517 0.02118 0.01430 -0.0532 0.0141 1.0000
10.500 1.3652 0.02202 0.01524 -0.0512 0.0135 1.0000
10.750 1.3756 0.02293 0.01624 -0.0487 0.0128 1.0000
11.000 1.3841 0.02395 0.01735 -0.0461 0.0123 1.0000
11.250 1.3903 0.02513 0.01862 -0.0434 0.0119 1.0000
11.500 1.3934 0.02657 0.02016 -0.0406 0.0116 1.0000
11.750 1.3929 0.02832 0.02202 -0.0377 0.0113 1.0000
12.000 1.3887 0.03049 0.02433 -0.0348 0.0110 1.0000
12.250 1.3921 0.03220 0.02616 -0.0329 0.0109 1.0000
12.500 1.3946 0.03407 0.02816 -0.0312 0.0107 1.0000
12.750 1.3955 0.03622 0.03044 -0.0297 0.0105 1.0000
13.000 1.3954 0.03858 0.03292 -0.0285 0.0105 1.0000
13.250 1.3973 0.04088 0.03534 -0.0277 0.0101 1.0000
13.500 1.3962 0.04362 0.03821 -0.0271 0.0101 1.0000
13.750 1.3946 0.04657 0.04129 -0.0268 0.0098 1.0000
14.000 1.3920 0.04981 0.04466 -0.0269 0.0097 1.0000
14.250 1.3888 0.05326 0.04824 -0.0272 0.0096 1.0000
14.500 1.3837 0.05715 0.05227 -0.0278 0.0095 1.0000
14.750 1.3785 0.06118 0.05644 -0.0287 0.0094 1.0000
15.000 1.3733 0.06541 0.06080 -0.0300 0.0093 1.0000
15.250 1.3663 0.07007 0.06562 -0.0315 0.0092 1.0000
15.500 1.3589 0.07494 0.07064 -0.0333 0.0092 1.0000
15.750 1.3509 0.08014 0.07598 -0.0354 0.0092 1.0000
16.000 1.3425 0.08557 0.08155 -0.0379 0.0091 1.0000
16.250 1.3318 0.09156 0.08771 -0.0406 0.0091 1.0000
16.500 1.3217 0.09767 0.09397 -0.0437 0.0091 1.0000
16.750 1.3102 0.10423 0.10068 -0.0471 0.0091 1.0000
17.000 1.2978 0.11118 0.10779 -0.0508 0.0091 1.0000
17.250 1.2852 0.11841 0.11518 -0.0549 0.0091 1.0000
17.500 1.2717 0.12605 0.12298 -0.0594 0.0091 1.0000
17.750 1.2573 0.13411 0.13120 -0.0643 0.0092 1.0000
18.000 1.2417 0.14273 0.13998 -0.0696 0.0092 1.0000
18.250 1.2245 0.15212 0.14954 -0.0756 0.0093 1.0000
18.500 1.1999 0.16410 0.16172 -0.0834 0.0095 1.0000
18.750 1.1689 0.17880 0.17662 -0.0929 0.0098 1.0000
19.000 1.0539 0.23638 0.23430 -0.1202 0.0197 1.0000
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Polar data table (+)
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