S2048 (s2048-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2048 (s2048-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.32 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2048-il-1000000.txt Download as CSV file: xf-s2048-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S2048
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4759 0.12602 0.12427 -0.0179 1.0000 0.0082
-11.500 -0.4731 0.12170 0.11996 -0.0197 1.0000 0.0091
-7.500 -0.5425 0.02579 0.02277 -0.0633 0.9882 0.0076
-7.250 -0.5156 0.02235 0.01892 -0.0650 0.9862 0.0081
-7.000 -0.4868 0.01896 0.01506 -0.0665 0.9847 0.0087
-6.750 -0.4542 0.01767 0.01354 -0.0680 0.9838 0.0093
-6.500 -0.4198 0.01732 0.01306 -0.0696 0.9831 0.0096
-6.250 -0.4001 0.01393 0.00929 -0.0690 0.9787 0.0107
-6.000 -0.3689 0.01320 0.00850 -0.0700 0.9768 0.0113
-5.750 -0.3364 0.01250 0.00773 -0.0713 0.9753 0.0120
-5.500 -0.3025 0.01210 0.00728 -0.0727 0.9741 0.0133
-5.250 -0.2690 0.01168 0.00680 -0.0740 0.9728 0.0140
-5.000 -0.2358 0.01112 0.00615 -0.0753 0.9715 0.0146
-4.750 -0.2084 0.00977 0.00467 -0.0755 0.9685 0.0155
-4.500 -0.1831 0.00915 0.00399 -0.0750 0.9636 0.0166
-4.250 -0.1537 0.00875 0.00356 -0.0753 0.9603 0.0181
-4.000 -0.1242 0.00838 0.00314 -0.0757 0.9573 0.0192
-3.750 -0.0984 0.00808 0.00280 -0.0752 0.9520 0.0201
-3.500 -0.0714 0.00781 0.00248 -0.0749 0.9468 0.0209
-3.250 -0.0433 0.00757 0.00218 -0.0748 0.9427 0.0216
-3.000 -0.0176 0.00728 0.00188 -0.0742 0.9355 0.0275
-2.750 0.0091 0.00690 0.00163 -0.0740 0.9296 0.0684
-2.500 0.0349 0.00655 0.00146 -0.0736 0.9207 0.1204
-2.250 0.0610 0.00613 0.00129 -0.0733 0.9114 0.2009
-2.000 0.0862 0.00554 0.00110 -0.0730 0.8998 0.3393
-1.750 0.1116 0.00510 0.00097 -0.0727 0.8864 0.4582
-1.500 0.1375 0.00481 0.00092 -0.0723 0.8722 0.5545
-0.750 0.2184 0.00463 0.00086 -0.0715 0.8339 0.6618
-0.500 0.2457 0.00461 0.00086 -0.0712 0.8227 0.6860
-0.250 0.2727 0.00459 0.00087 -0.0710 0.8115 0.7116
0.000 0.2998 0.00459 0.00089 -0.0707 0.8003 0.7340
0.250 0.3269 0.00460 0.00090 -0.0704 0.7886 0.7527
0.750 0.3811 0.00463 0.00094 -0.0699 0.7632 0.7849
1.000 0.4080 0.00465 0.00097 -0.0696 0.7487 0.7999
1.250 0.4346 0.00469 0.00100 -0.0693 0.7330 0.8155
1.500 0.4611 0.00471 0.00104 -0.0689 0.7164 0.8324
1.750 0.4870 0.00475 0.00108 -0.0684 0.6958 0.8519
2.000 0.5120 0.00481 0.00114 -0.0677 0.6709 0.8747
2.250 0.5355 0.00489 0.00121 -0.0666 0.6399 0.9037
2.500 0.5571 0.00505 0.00128 -0.0651 0.5925 0.9448
2.750 0.5899 0.00552 0.00140 -0.0664 0.5011 0.9927
3.000 0.6142 0.00600 0.00158 -0.0659 0.4280 1.0000
3.250 0.6386 0.00637 0.00174 -0.0654 0.3781 1.0000
3.500 0.6631 0.00674 0.00191 -0.0649 0.3313 1.0000
3.750 0.6881 0.00707 0.00208 -0.0645 0.2938 1.0000
4.000 0.7134 0.00737 0.00226 -0.0641 0.2637 1.0000
4.250 0.7388 0.00766 0.00244 -0.0638 0.2366 1.0000
4.500 0.7643 0.00794 0.00263 -0.0634 0.2128 1.0000
4.750 0.7899 0.00820 0.00282 -0.0631 0.1922 1.0000
5.000 0.8151 0.00851 0.00304 -0.0627 0.1680 1.0000
5.250 0.8397 0.00889 0.00329 -0.0623 0.1379 1.0000
5.500 0.8631 0.00940 0.00361 -0.0616 0.0999 1.0000
6.000 0.9104 0.01037 0.00432 -0.0604 0.0516 1.0000
6.250 0.9349 0.01075 0.00465 -0.0599 0.0413 1.0000
6.500 0.9591 0.01117 0.00504 -0.0594 0.0321 1.0000
6.750 0.9842 0.01147 0.00534 -0.0590 0.0277 1.0000
7.000 1.0084 0.01187 0.00573 -0.0584 0.0221 1.0000
7.250 1.0324 0.01228 0.00611 -0.0579 0.0171 1.0000
7.500 1.0556 0.01280 0.00661 -0.0572 0.0116 1.0000
7.750 1.0785 0.01337 0.00723 -0.0564 0.0089 1.0000
8.000 1.1009 0.01398 0.00786 -0.0555 0.0073 1.0000
8.250 1.1215 0.01481 0.00881 -0.0543 0.0065 1.0000
8.500 1.1438 0.01539 0.00946 -0.0534 0.0061 1.0000
8.750 1.1651 0.01605 0.01020 -0.0524 0.0057 1.0000
9.000 1.1862 0.01672 0.01094 -0.0514 0.0053 1.0000
9.250 1.2068 0.01740 0.01169 -0.0504 0.0050 1.0000
9.500 1.2255 0.01826 0.01265 -0.0491 0.0047 1.0000
9.750 1.2413 0.01942 0.01393 -0.0473 0.0045 1.0000
10.000 1.2533 0.02096 0.01564 -0.0450 0.0043 1.0000
10.250 1.2642 0.02257 0.01743 -0.0427 0.0042 1.0000
10.500 1.2705 0.02471 0.01979 -0.0397 0.0041 1.0000
10.750 1.2852 0.02566 0.02086 -0.0380 0.0041 1.0000
11.000 1.2935 0.02700 0.02235 -0.0353 0.0040 1.0000
11.250 1.2984 0.02844 0.02395 -0.0322 0.0040 1.0000
11.500 1.3035 0.02978 0.02543 -0.0293 0.0040 1.0000
11.750 1.3076 0.03118 0.02697 -0.0266 0.0039 1.0000
12.000 1.3059 0.03317 0.02914 -0.0235 0.0039 1.0000
12.250 1.3057 0.03501 0.03114 -0.0210 0.0038 1.0000
12.500 1.3025 0.03722 0.03352 -0.0186 0.0037 1.0000
12.750 1.2993 0.03952 0.03598 -0.0167 0.0037 1.0000
13.000 1.2915 0.04247 0.03911 -0.0152 0.0036 1.0000
13.250 1.2813 0.04594 0.04275 -0.0144 0.0036 1.0000
13.500 1.2694 0.04993 0.04692 -0.0143 0.0036 1.0000
13.750 1.2488 0.05559 0.05279 -0.0154 0.0036 1.0000
14.000 1.2387 0.06034 0.05768 -0.0173 0.0035 1.0000
14.250 1.2175 0.06761 0.06514 -0.0211 0.0035 1.0000
14.500 1.1965 0.07591 0.07363 -0.0262 0.0036 1.0000
14.750 1.1707 0.08630 0.08419 -0.0329 0.0037 1.0000
15.000 1.1450 0.09745 0.09550 -0.0401 0.0037 1.0000
15.250 1.1243 0.10772 0.10588 -0.0464 0.0037 1.0000
15.500 1.0907 0.12152 0.11980 -0.0545 0.0038 1.0000
15.750 1.0617 0.13471 0.13310 -0.0621 0.0039 1.0000
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Polar data table (+)
Polar graphs
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