CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.9 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cast102-il-1000000.txt Download as CSV file: xf-cast102-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: CAST 10-2/DOA 2 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5060 0.07657 0.07489 -0.0640 0.9955 0.0120
-10.000 -0.5189 0.06829 0.06651 -0.0726 0.9902 0.0120
-9.750 -0.5290 0.06258 0.06068 -0.0778 0.9834 0.0121
-9.500 -0.5404 0.05875 0.05674 -0.0783 0.9729 0.0121
-9.250 -0.5454 0.05556 0.05342 -0.0776 0.9645 0.0122
-9.000 -0.5460 0.05251 0.05024 -0.0767 0.9579 0.0123
-8.750 -0.5430 0.04950 0.04710 -0.0759 0.9519 0.0125
-8.500 -0.5377 0.04652 0.04395 -0.0749 0.9468 0.0128
-8.250 -0.5294 0.04342 0.04067 -0.0739 0.9424 0.0133
-8.000 -0.5161 0.03894 0.03570 -0.0714 0.9378 0.0148
-7.750 -0.5055 0.03590 0.03236 -0.0699 0.9337 0.0148
-7.500 -0.5024 0.03012 0.02626 -0.0684 0.9295 0.0153
-7.250 -0.4826 0.02853 0.02458 -0.0681 0.9268 0.0155
-7.000 -0.4617 0.02708 0.02301 -0.0678 0.9240 0.0158
-6.750 -0.4400 0.02563 0.02143 -0.0674 0.9211 0.0162
-6.500 -0.4177 0.02411 0.01975 -0.0669 0.9184 0.0168
-6.250 -0.3906 0.02427 0.01961 -0.0661 0.9159 0.0187
-6.000 -0.3723 0.01735 0.01201 -0.0640 0.9132 0.0151
-5.750 -0.3465 0.01573 0.01025 -0.0637 0.9113 0.0151
-5.500 -0.3207 0.01443 0.00887 -0.0636 0.9091 0.0153
-5.250 -0.2948 0.01354 0.00795 -0.0634 0.9067 0.0156
-5.000 -0.2687 0.01286 0.00724 -0.0633 0.9044 0.0159
-4.750 -0.2426 0.01227 0.00662 -0.0632 0.9023 0.0162
-4.500 -0.2162 0.01179 0.00612 -0.0631 0.9003 0.0167
-4.250 -0.1895 0.01142 0.00573 -0.0630 0.8981 0.0175
-4.000 -0.1627 0.01097 0.00526 -0.0630 0.8962 0.0181
-3.750 -0.1357 0.01060 0.00487 -0.0631 0.8941 0.0186
-3.500 -0.1089 0.01018 0.00443 -0.0631 0.8917 0.0190
-3.250 -0.0830 0.00956 0.00378 -0.0630 0.8895 0.0198
-3.000 -0.0553 0.00927 0.00348 -0.0632 0.8876 0.0206
-2.750 -0.0272 0.00905 0.00326 -0.0634 0.8858 0.0217
-2.500 0.0010 0.00890 0.00309 -0.0637 0.8839 0.0231
-2.250 0.0294 0.00871 0.00288 -0.0639 0.8819 0.0241
-2.000 0.0576 0.00844 0.00261 -0.0642 0.8797 0.0263
-1.750 0.0861 0.00827 0.00244 -0.0645 0.8766 0.0288
-1.500 0.1143 0.00805 0.00221 -0.0646 0.8724 0.0365
-1.250 0.1356 0.00581 0.00177 -0.0649 0.8677 0.6084
-1.000 0.1638 0.00571 0.00176 -0.0649 0.8627 0.6480
-0.750 0.1924 0.00565 0.00171 -0.0651 0.8574 0.6631
-0.500 0.2209 0.00562 0.00167 -0.0651 0.8514 0.6732
-0.250 0.2493 0.00557 0.00162 -0.0652 0.8436 0.6841
0.000 0.2778 0.00557 0.00159 -0.0653 0.8368 0.6945
0.250 0.3065 0.00552 0.00157 -0.0655 0.8298 0.7002
0.500 0.3353 0.00551 0.00155 -0.0657 0.8242 0.7056
0.750 0.3643 0.00551 0.00155 -0.0660 0.8178 0.7104
1.000 0.3931 0.00550 0.00153 -0.0663 0.8108 0.7139
1.250 0.4219 0.00548 0.00154 -0.0666 0.8040 0.7177
1.500 0.4505 0.00548 0.00153 -0.0668 0.7947 0.7215
1.750 0.4787 0.00550 0.00152 -0.0668 0.7790 0.7253
2.000 0.5062 0.00555 0.00151 -0.0668 0.7533 0.7290
2.250 0.5324 0.00567 0.00153 -0.0665 0.7175 0.7331
2.500 0.5535 0.00615 0.00165 -0.0651 0.6240 0.7376
2.750 0.5703 0.00704 0.00197 -0.0632 0.4936 0.7421
3.000 0.5901 0.00772 0.00225 -0.0619 0.3957 0.7465
3.250 0.6131 0.00817 0.00246 -0.0613 0.3368 0.7512
3.500 0.6376 0.00851 0.00264 -0.0608 0.2949 0.7562
3.750 0.6621 0.00885 0.00282 -0.0604 0.2567 0.7611
4.000 0.6868 0.00914 0.00301 -0.0600 0.2262 0.7666
4.250 0.7121 0.00941 0.00319 -0.0598 0.2032 0.7724
4.500 0.7374 0.00965 0.00337 -0.0595 0.1842 0.7781
4.750 0.7628 0.00988 0.00357 -0.0592 0.1671 0.7842
5.250 0.8134 0.01035 0.00397 -0.0586 0.1396 0.7976
5.500 0.8385 0.01060 0.00419 -0.0583 0.1277 0.8054
5.750 0.8635 0.01082 0.00441 -0.0580 0.1159 0.8135
6.000 0.8886 0.01105 0.00463 -0.0577 0.1058 0.8224
6.250 0.9131 0.01129 0.00487 -0.0572 0.0951 0.8324
6.500 0.9370 0.01157 0.00514 -0.0567 0.0828 0.8434
6.750 0.9598 0.01193 0.00545 -0.0560 0.0671 0.8567
7.000 0.9791 0.01255 0.00593 -0.0546 0.0377 0.8737
7.250 0.9994 0.01301 0.00639 -0.0533 0.0285 0.8960
7.500 1.0190 0.01325 0.00676 -0.0517 0.0265 0.9284
7.750 1.0397 0.01356 0.00715 -0.0504 0.0243 1.0000
8.000 1.0625 0.01407 0.00769 -0.0497 0.0225 1.0000
8.250 1.0860 0.01446 0.00811 -0.0492 0.0217 1.0000
8.500 1.1089 0.01489 0.00858 -0.0486 0.0206 1.0000
8.750 1.1309 0.01539 0.00909 -0.0478 0.0196 1.0000
9.000 1.1506 0.01609 0.00983 -0.0467 0.0184 1.0000
9.250 1.1692 0.01683 0.01066 -0.0453 0.0177 1.0000
9.500 1.1904 0.01728 0.01115 -0.0444 0.0174 1.0000
9.750 1.2097 0.01778 0.01170 -0.0432 0.0169 1.0000
10.000 1.2279 0.01833 0.01230 -0.0417 0.0164 1.0000
10.250 1.2454 0.01893 0.01296 -0.0402 0.0159 1.0000
10.500 1.2624 0.01957 0.01365 -0.0387 0.0155 1.0000
10.750 1.2787 0.02026 0.01439 -0.0371 0.0151 1.0000
11.000 1.2933 0.02105 0.01523 -0.0353 0.0147 1.0000
11.250 1.3029 0.02224 0.01649 -0.0328 0.0142 1.0000
11.500 1.3087 0.02373 0.01810 -0.0299 0.0138 1.0000
11.750 1.3246 0.02442 0.01886 -0.0284 0.0137 1.0000
12.000 1.3387 0.02523 0.01975 -0.0268 0.0135 1.0000
12.250 1.3514 0.02616 0.02076 -0.0251 0.0132 1.0000
12.500 1.3629 0.02717 0.02185 -0.0233 0.0130 1.0000
12.750 1.3733 0.02827 0.02305 -0.0214 0.0128 1.0000
13.000 1.3832 0.02942 0.02428 -0.0196 0.0125 1.0000
13.250 1.3918 0.03067 0.02562 -0.0177 0.0123 1.0000
13.500 1.3995 0.03201 0.02706 -0.0159 0.0121 1.0000
13.750 1.4065 0.03341 0.02855 -0.0141 0.0119 1.0000
14.000 1.4125 0.03492 0.03015 -0.0123 0.0118 1.0000
14.250 1.4184 0.03645 0.03176 -0.0107 0.0116 1.0000
14.500 1.4226 0.03818 0.03356 -0.0092 0.0114 1.0000
14.750 1.4233 0.04026 0.03573 -0.0076 0.0112 1.0000
15.000 1.4194 0.04288 0.03846 -0.0059 0.0110 1.0000
15.250 1.4092 0.04628 0.04200 -0.0042 0.0109 1.0000
15.500 1.3925 0.05055 0.04645 -0.0027 0.0107 1.0000
15.750 1.3802 0.05467 0.05074 -0.0020 0.0106 1.0000
16.000 1.3766 0.05801 0.05420 -0.0022 0.0106 1.0000
16.250 1.3698 0.06199 0.05832 -0.0028 0.0105 1.0000
16.500 1.3619 0.06647 0.06295 -0.0040 0.0105 1.0000
16.750 1.3515 0.07167 0.06829 -0.0059 0.0104 1.0000
17.000 1.3389 0.07756 0.07434 -0.0085 0.0104 1.0000
17.250 1.3245 0.08412 0.08105 -0.0118 0.0104 1.0000
17.500 1.3073 0.09149 0.08858 -0.0157 0.0104 1.0000
17.750 1.2885 0.09939 0.09663 -0.0201 0.0104 1.0000
18.000 1.2675 0.10777 0.10515 -0.0247 0.0103 1.0000
18.250 1.2450 0.11658 0.11410 -0.0296 0.0103 1.0000
18.500 1.2217 0.12575 0.12340 -0.0348 0.0104 1.0000
18.750 1.1986 0.13510 0.13289 -0.0402 0.0104 1.0000
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