SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD2030-086-88 (sd2030-il) Reynolds number: 500,000 Max Cl/Cd: 80.98 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd2030-il-500000-n5.txt Download as CSV file: xf-sd2030-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4648 0.08500 0.08273 -0.0348 1.0000 0.0095
-9.000 -0.4744 0.08097 0.07874 -0.0354 1.0000 0.0095
-8.750 -0.4880 0.07713 0.07496 -0.0356 1.0000 0.0097
-8.500 -0.4995 0.07248 0.07035 -0.0383 0.9987 0.0097
-8.250 -0.4950 0.06204 0.05984 -0.0533 0.9917 0.0096
-8.000 -0.4892 0.05110 0.04869 -0.0640 0.9858 0.0096
-7.750 -0.4842 0.03948 0.03661 -0.0703 0.9806 0.0098
-7.500 -0.4802 0.02892 0.02527 -0.0723 0.9743 0.0100
-7.250 -0.4577 0.02473 0.02055 -0.0736 0.9720 0.0105
-7.000 -0.4311 0.02205 0.01745 -0.0746 0.9703 0.0109
-6.750 -0.4116 0.02011 0.01518 -0.0737 0.9651 0.0111
-6.500 -0.3860 0.01851 0.01329 -0.0737 0.9619 0.0113
-6.250 -0.3577 0.01735 0.01189 -0.0742 0.9595 0.0116
-6.000 -0.3283 0.01639 0.01074 -0.0748 0.9575 0.0117
-5.750 -0.3054 0.01471 0.00883 -0.0741 0.9534 0.0122
-5.500 -0.2807 0.01374 0.00773 -0.0737 0.9489 0.0126
-5.250 -0.2532 0.01298 0.00689 -0.0738 0.9457 0.0130
-5.000 -0.2247 0.01233 0.00615 -0.0741 0.9432 0.0133
-4.750 -0.2001 0.01188 0.00566 -0.0735 0.9381 0.0139
-4.500 -0.1737 0.01144 0.00518 -0.0733 0.9335 0.0146
-4.250 -0.1459 0.01095 0.00463 -0.0733 0.9300 0.0150
-4.000 -0.1199 0.01052 0.00414 -0.0729 0.9251 0.0154
-3.750 -0.0937 0.01014 0.00369 -0.0726 0.9198 0.0159
-3.500 -0.0655 0.00980 0.00329 -0.0726 0.9158 0.0164
-3.250 -0.0391 0.00954 0.00298 -0.0722 0.9100 0.0171
-3.000 -0.0119 0.00927 0.00266 -0.0720 0.9046 0.0183
-2.750 0.0160 0.00902 0.00238 -0.0720 0.8995 0.0210
-2.500 0.0427 0.00882 0.00218 -0.0717 0.8927 0.0257
-2.250 0.0703 0.00851 0.00198 -0.0716 0.8869 0.0558
-2.000 0.0965 0.00825 0.00184 -0.0714 0.8793 0.0920
-1.750 0.1237 0.00797 0.00169 -0.0713 0.8723 0.1400
-1.500 0.1495 0.00761 0.00158 -0.0710 0.8631 0.2182
-1.250 0.1757 0.00730 0.00148 -0.0708 0.8538 0.2966
-1.000 0.2008 0.00681 0.00139 -0.0705 0.8442 0.4318
-0.750 0.2234 0.00617 0.00134 -0.0696 0.8336 0.6204
-0.500 0.2456 0.00579 0.00140 -0.0682 0.8227 0.7596
-0.250 0.2696 0.00569 0.00144 -0.0670 0.8117 0.8203
0.000 0.2943 0.00568 0.00146 -0.0660 0.7997 0.8562
0.250 0.3189 0.00569 0.00147 -0.0650 0.7869 0.8817
0.500 0.3436 0.00572 0.00149 -0.0640 0.7732 0.9020
0.750 0.3681 0.00576 0.00150 -0.0630 0.7577 0.9192
1.000 0.3929 0.00582 0.00151 -0.0621 0.7394 0.9350
1.250 0.4190 0.00590 0.00152 -0.0615 0.7186 0.9487
1.500 0.4471 0.00600 0.00153 -0.0614 0.6933 0.9603
1.750 0.4761 0.00615 0.00156 -0.0616 0.6617 0.9706
2.000 0.5078 0.00637 0.00161 -0.0624 0.6213 0.9780
2.250 0.5380 0.00665 0.00168 -0.0630 0.5733 0.9848
2.500 0.5685 0.00702 0.00180 -0.0639 0.5169 0.9904
2.750 0.5980 0.00744 0.00196 -0.0646 0.4571 0.9964
3.000 0.6226 0.00785 0.00213 -0.0642 0.4030 1.0000
3.250 0.6417 0.00819 0.00229 -0.0626 0.3634 1.0000
3.500 0.6620 0.00854 0.00246 -0.0613 0.3237 1.0000
3.750 0.6836 0.00889 0.00266 -0.0602 0.2871 1.0000
4.250 0.7289 0.00956 0.00307 -0.0585 0.2262 1.0000
4.500 0.7519 0.00992 0.00330 -0.0577 0.1976 1.0000
4.750 0.7750 0.01028 0.00354 -0.0569 0.1707 1.0000
5.000 0.7983 0.01064 0.00382 -0.0562 0.1466 1.0000
5.250 0.8218 0.01100 0.00409 -0.0556 0.1274 1.0000
5.500 0.8456 0.01133 0.00437 -0.0550 0.1116 1.0000
5.750 0.8693 0.01167 0.00466 -0.0543 0.0972 1.0000
6.000 0.8928 0.01204 0.00498 -0.0537 0.0837 1.0000
6.250 0.9161 0.01242 0.00534 -0.0530 0.0722 1.0000
6.500 0.9393 0.01282 0.00570 -0.0523 0.0618 1.0000
6.750 0.9623 0.01322 0.00607 -0.0516 0.0526 1.0000
7.000 0.9855 0.01361 0.00645 -0.0509 0.0449 1.0000
7.250 1.0082 0.01403 0.00686 -0.0502 0.0386 1.0000
7.500 1.0313 0.01442 0.00728 -0.0495 0.0342 1.0000
7.750 1.0535 0.01487 0.00774 -0.0487 0.0293 1.0000
8.000 1.0762 0.01527 0.00818 -0.0479 0.0262 1.0000
8.250 1.0976 0.01579 0.00868 -0.0470 0.0210 1.0000
8.500 1.1187 0.01632 0.00921 -0.0461 0.0155 1.0000
8.750 1.1385 0.01698 0.00984 -0.0449 0.0104 1.0000
9.000 1.1584 0.01761 0.01054 -0.0438 0.0082 1.0000
9.250 1.1772 0.01835 0.01133 -0.0425 0.0068 1.0000
9.500 1.1965 0.01900 0.01207 -0.0412 0.0063 1.0000
9.750 1.2150 0.01968 0.01286 -0.0399 0.0059 1.0000
10.000 1.2326 0.02042 0.01369 -0.0385 0.0056 1.0000
10.250 1.2486 0.02122 0.01460 -0.0368 0.0052 1.0000
10.500 1.2628 0.02205 0.01553 -0.0348 0.0050 1.0000
10.750 1.2748 0.02300 0.01659 -0.0325 0.0047 1.0000
11.000 1.2846 0.02409 0.01782 -0.0301 0.0045 1.0000
11.250 1.2902 0.02548 0.01936 -0.0271 0.0043 1.0000
11.500 1.2998 0.02655 0.02054 -0.0248 0.0041 1.0000
11.750 1.3089 0.02766 0.02179 -0.0226 0.0040 1.0000
12.000 1.3166 0.02887 0.02313 -0.0204 0.0039 1.0000
12.250 1.3235 0.03018 0.02457 -0.0183 0.0038 1.0000
12.500 1.3275 0.03172 0.02627 -0.0160 0.0037 1.0000
12.750 1.3297 0.03346 0.02815 -0.0139 0.0037 1.0000
13.000 1.3300 0.03544 0.03029 -0.0118 0.0036 1.0000
13.250 1.3292 0.03758 0.03260 -0.0101 0.0035 1.0000
13.500 1.3271 0.03998 0.03515 -0.0086 0.0035 1.0000
13.750 1.3238 0.04263 0.03796 -0.0075 0.0034 1.0000
14.000 1.3182 0.04570 0.04121 -0.0068 0.0034 1.0000
14.250 1.3113 0.04917 0.04486 -0.0067 0.0033 1.0000
14.500 1.3004 0.05341 0.04929 -0.0072 0.0033 1.0000
14.750 1.2900 0.05801 0.05405 -0.0084 0.0033 1.0000
15.000 1.2784 0.06323 0.05945 -0.0106 0.0032 1.0000
15.250 1.2614 0.06991 0.06631 -0.0138 0.0033 1.0000
15.500 1.2423 0.07767 0.07426 -0.0182 0.0033 1.0000
15.750 1.2228 0.08614 0.08291 -0.0232 0.0033 1.0000
16.000 1.2016 0.09547 0.09241 -0.0288 0.0033 1.0000
16.250 1.1785 0.10543 0.10250 -0.0346 0.0034 1.0000
16.500 1.1532 0.11615 0.11337 -0.0407 0.0034 1.0000
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Polar data table (+)
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