SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2030-086-88 (sd2030-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.43 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2030-il-1000000.txt Download as CSV file: xf-sd2030-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SD2030-086-88
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4603 0.08496 0.08337 -0.0325 1.0000 0.0118
-8.750 -0.4692 0.08186 0.08031 -0.0322 1.0000 0.0122
-8.500 -0.4821 0.07892 0.07741 -0.0313 1.0000 0.0123
-8.250 -0.4875 0.07389 0.07241 -0.0357 0.9985 0.0124
-8.000 -0.4715 0.06426 0.06272 -0.0516 0.9944 0.0129
-7.250 -0.4417 0.02995 0.02713 -0.0751 0.9810 0.0146
-7.000 -0.4202 0.02727 0.02426 -0.0761 0.9777 0.0151
-6.750 -0.3919 0.02596 0.02286 -0.0776 0.9760 0.0156
-6.500 -0.3687 0.01940 0.01552 -0.0781 0.9737 0.0133
-6.250 -0.3405 0.01665 0.01239 -0.0789 0.9722 0.0130
-6.000 -0.3099 0.01532 0.01085 -0.0798 0.9708 0.0133
-5.750 -0.2882 0.01455 0.00994 -0.0786 0.9656 0.0137
-5.500 -0.2606 0.01365 0.00889 -0.0786 0.9625 0.0139
-5.250 -0.2333 0.01225 0.00730 -0.0786 0.9597 0.0143
-5.000 -0.2072 0.01090 0.00583 -0.0784 0.9570 0.0147
-4.750 -0.1853 0.01018 0.00505 -0.0772 0.9514 0.0151
-4.500 -0.1595 0.00961 0.00442 -0.0767 0.9473 0.0156
-4.250 -0.1330 0.00914 0.00390 -0.0764 0.9438 0.0160
-4.000 -0.1081 0.00877 0.00349 -0.0757 0.9386 0.0165
-3.750 -0.0820 0.00844 0.00313 -0.0753 0.9336 0.0174
-3.500 -0.0552 0.00811 0.00274 -0.0750 0.9294 0.0183
-3.250 -0.0293 0.00785 0.00243 -0.0745 0.9232 0.0191
-3.000 -0.0027 0.00758 0.00211 -0.0741 0.9177 0.0202
-2.750 0.0242 0.00733 0.00182 -0.0738 0.9119 0.0234
-2.500 0.0505 0.00706 0.00161 -0.0734 0.9048 0.0395
-2.250 0.0767 0.00673 0.00144 -0.0731 0.8977 0.0897
-2.000 0.1027 0.00640 0.00131 -0.0727 0.8896 0.1525
-1.750 0.1285 0.00603 0.00120 -0.0725 0.8814 0.2397
-1.500 0.1541 0.00564 0.00110 -0.0722 0.8732 0.3474
-1.250 0.1792 0.00520 0.00103 -0.0718 0.8641 0.4733
-1.000 0.2032 0.00468 0.00098 -0.0712 0.8555 0.6376
-0.750 0.2264 0.00431 0.00102 -0.0701 0.8462 0.7762
-0.500 0.2519 0.00423 0.00104 -0.0694 0.8368 0.8241
-0.250 0.2779 0.00421 0.00105 -0.0688 0.8276 0.8525
0.000 0.3035 0.00421 0.00106 -0.0680 0.8175 0.8767
0.250 0.3290 0.00423 0.00108 -0.0673 0.8066 0.8967
0.500 0.3543 0.00425 0.00110 -0.0665 0.7954 0.9126
0.750 0.3791 0.00429 0.00112 -0.0656 0.7835 0.9266
1.000 0.4034 0.00433 0.00114 -0.0646 0.7703 0.9395
1.250 0.4275 0.00438 0.00116 -0.0636 0.7555 0.9514
1.500 0.4525 0.00443 0.00118 -0.0627 0.7380 0.9627
1.750 0.4794 0.00452 0.00120 -0.0624 0.7170 0.9733
2.000 0.5097 0.00466 0.00123 -0.0628 0.6884 0.9815
2.250 0.5437 0.00485 0.00128 -0.0642 0.6499 0.9864
2.500 0.5779 0.00514 0.00136 -0.0658 0.5976 0.9904
2.750 0.6102 0.00551 0.00148 -0.0670 0.5362 0.9948
3.000 0.6435 0.00592 0.00162 -0.0685 0.4739 0.9984
3.250 0.6679 0.00629 0.00176 -0.0681 0.4194 1.0000
3.500 0.6851 0.00661 0.00190 -0.0661 0.3764 1.0000
3.750 0.7036 0.00696 0.00207 -0.0643 0.3321 1.0000
4.000 0.7244 0.00730 0.00224 -0.0631 0.2919 1.0000
4.250 0.7465 0.00765 0.00243 -0.0621 0.2549 1.0000
4.500 0.7698 0.00797 0.00262 -0.0613 0.2252 1.0000
4.750 0.7932 0.00830 0.00283 -0.0606 0.1952 1.0000
5.000 0.8168 0.00864 0.00305 -0.0599 0.1683 1.0000
5.250 0.8406 0.00898 0.00328 -0.0593 0.1454 1.0000
5.500 0.8648 0.00930 0.00352 -0.0587 0.1253 1.0000
5.750 0.8885 0.00966 0.00379 -0.0581 0.1057 1.0000
6.000 0.9123 0.01001 0.00406 -0.0575 0.0877 1.0000
6.250 0.9359 0.01038 0.00436 -0.0568 0.0725 1.0000
6.500 0.9598 0.01073 0.00465 -0.0562 0.0614 1.0000
6.750 0.9837 0.01108 0.00498 -0.0556 0.0524 1.0000
7.000 1.0071 0.01146 0.00531 -0.0550 0.0442 1.0000
7.250 1.0314 0.01175 0.00562 -0.0545 0.0399 1.0000
7.500 1.0545 0.01217 0.00599 -0.0538 0.0334 1.0000
7.750 1.0787 0.01245 0.00630 -0.0532 0.0306 1.0000
8.000 1.1015 0.01286 0.00670 -0.0525 0.0257 1.0000
8.250 1.1248 0.01323 0.00707 -0.0519 0.0212 1.0000
8.500 1.1451 0.01389 0.00764 -0.0507 0.0125 1.0000
8.750 1.1656 0.01453 0.00829 -0.0496 0.0093 1.0000
9.000 1.1868 0.01509 0.00891 -0.0486 0.0081 1.0000
9.250 1.2077 0.01564 0.00952 -0.0475 0.0075 1.0000
9.500 1.2273 0.01632 0.01026 -0.0463 0.0069 1.0000
9.750 1.2433 0.01733 0.01139 -0.0444 0.0061 1.0000
10.000 1.2618 0.01803 0.01218 -0.0431 0.0059 1.0000
10.250 1.2801 0.01870 0.01293 -0.0417 0.0055 1.0000
10.500 1.2972 0.01944 0.01375 -0.0401 0.0054 1.0000
10.750 1.3120 0.02029 0.01469 -0.0382 0.0052 1.0000
11.000 1.3248 0.02110 0.01559 -0.0359 0.0051 1.0000
11.250 1.3351 0.02203 0.01665 -0.0333 0.0050 1.0000
11.500 1.3458 0.02292 0.01762 -0.0309 0.0048 1.0000
11.750 1.3543 0.02397 0.01877 -0.0283 0.0047 1.0000
12.000 1.3626 0.02503 0.01994 -0.0258 0.0046 1.0000
12.250 1.3680 0.02632 0.02134 -0.0230 0.0045 1.0000
12.500 1.3724 0.02769 0.02283 -0.0204 0.0045 1.0000
12.750 1.3747 0.02925 0.02451 -0.0177 0.0044 1.0000
13.000 1.3747 0.03106 0.02646 -0.0151 0.0044 1.0000
13.250 1.3718 0.03318 0.02872 -0.0126 0.0043 1.0000
13.500 1.3659 0.03569 0.03139 -0.0103 0.0042 1.0000
13.750 1.3596 0.03840 0.03426 -0.0085 0.0042 1.0000
14.000 1.3520 0.04143 0.03745 -0.0071 0.0042 1.0000
14.250 1.3295 0.04638 0.04264 -0.0062 0.0040 1.0000
14.500 1.3243 0.04970 0.04609 -0.0062 0.0041 1.0000
14.750 1.3069 0.05491 0.05149 -0.0071 0.0040 1.0000
15.500 1.2506 0.07516 0.07230 -0.0164 0.0039 1.0000
15.750 1.2375 0.08201 0.07927 -0.0203 0.0040 1.0000
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Polar data table (+)
Polar graphs
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