GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 399 AIRFOIL (goe399-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.09 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe399-il-1000000.txt Download as CSV file: xf-goe399-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 399 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3656 0.08500 0.08345 -0.0267 1.0000 0.0113
-7.750 -0.3681 0.08310 0.08158 -0.0257 1.0000 0.0114
-7.500 -0.3724 0.08213 0.08065 -0.0234 1.0000 0.0120
-6.750 -0.3325 0.01488 0.01128 -0.0835 0.9764 0.0118
-6.500 -0.2985 0.01467 0.01105 -0.0849 0.9730 0.0124
-6.250 -0.2652 0.01373 0.00993 -0.0863 0.9698 0.0132
-6.000 -0.2391 0.01289 0.00891 -0.0860 0.9616 0.0140
-5.750 -0.2081 0.01235 0.00823 -0.0867 0.9557 0.0147
-5.500 -0.1838 0.01121 0.00688 -0.0861 0.9451 0.0161
-5.250 -0.1557 0.01132 0.00700 -0.0860 0.9348 0.0170
-5.000 -0.1281 0.01143 0.00708 -0.0857 0.9223 0.0183
-4.750 -0.1016 0.01130 0.00685 -0.0853 0.9068 0.0194
-4.500 -0.0774 0.01030 0.00560 -0.0845 0.8881 0.0208
-4.250 -0.0515 0.01016 0.00537 -0.0840 0.8696 0.0221
-4.000 -0.0251 0.01019 0.00533 -0.0835 0.8509 0.0234
-3.750 0.0010 0.01017 0.00521 -0.0830 0.8324 0.0249
-3.500 0.0273 0.01013 0.00506 -0.0825 0.8154 0.0262
-3.250 0.0540 0.01019 0.00502 -0.0821 0.8003 0.0268
-3.000 0.0778 0.00885 0.00345 -0.0814 0.7872 0.0292
-2.750 0.1043 0.00871 0.00326 -0.0810 0.7749 0.0309
-2.500 0.1307 0.00851 0.00298 -0.0806 0.7636 0.0322
-2.250 0.1571 0.00832 0.00271 -0.0802 0.7528 0.0335
-2.000 0.1835 0.00813 0.00245 -0.0798 0.7427 0.0346
-1.750 0.2101 0.00791 0.00218 -0.0794 0.7337 0.0352
-1.500 0.2366 0.00775 0.00195 -0.0790 0.7250 0.0358
-1.250 0.2632 0.00756 0.00170 -0.0787 0.7160 0.0366
-1.000 0.2893 0.00726 0.00133 -0.0782 0.7068 0.0401
-0.750 0.3159 0.00717 0.00120 -0.0778 0.6972 0.0425
-0.500 0.3428 0.00710 0.00110 -0.0775 0.6863 0.0450
-0.250 0.3697 0.00706 0.00101 -0.0772 0.6753 0.0474
0.000 0.3963 0.00697 0.00093 -0.0769 0.6634 0.0600
0.250 0.4229 0.00693 0.00090 -0.0765 0.6503 0.0790
0.500 0.4496 0.00691 0.00087 -0.0762 0.6380 0.0925
0.750 0.4760 0.00685 0.00086 -0.0759 0.6259 0.1217
1.000 0.5015 0.00660 0.00090 -0.0755 0.6129 0.2509
1.250 0.5667 0.00498 0.00105 -0.0847 0.5935 1.0000
1.500 0.5915 0.00513 0.00107 -0.0840 0.5669 1.0000
1.750 0.6165 0.00529 0.00110 -0.0833 0.5416 1.0000
2.000 0.6415 0.00545 0.00115 -0.0827 0.5171 1.0000
2.250 0.6663 0.00564 0.00123 -0.0820 0.4922 1.0000
2.500 0.6908 0.00585 0.00131 -0.0814 0.4686 1.0000
2.750 0.7159 0.00602 0.00141 -0.0808 0.4504 1.0000
3.000 0.7410 0.00619 0.00150 -0.0802 0.4341 1.0000
3.250 0.7663 0.00636 0.00162 -0.0797 0.4202 1.0000
3.500 0.7916 0.00651 0.00173 -0.0792 0.4073 1.0000
3.750 0.8169 0.00667 0.00184 -0.0786 0.3956 1.0000
4.000 0.8422 0.00683 0.00196 -0.0781 0.3824 1.0000
4.250 0.8674 0.00700 0.00210 -0.0776 0.3680 1.0000
4.500 0.8922 0.00719 0.00223 -0.0770 0.3473 1.0000
4.750 0.9153 0.00755 0.00241 -0.0762 0.3061 1.0000
5.000 0.9355 0.00818 0.00273 -0.0749 0.2439 1.0000
5.250 0.9564 0.00877 0.00307 -0.0738 0.1945 1.0000
5.500 0.9701 0.01009 0.00381 -0.0716 0.0791 1.0000
5.750 0.9924 0.01055 0.00415 -0.0706 0.0599 1.0000
6.000 1.0165 0.01082 0.00443 -0.0700 0.0538 1.0000
6.250 1.0400 0.01114 0.00474 -0.0692 0.0482 1.0000
6.500 1.0639 0.01142 0.00505 -0.0686 0.0431 1.0000
6.750 1.0871 0.01175 0.00534 -0.0678 0.0342 1.0000
7.000 1.1085 0.01227 0.00574 -0.0668 0.0201 1.0000
7.250 1.1306 0.01273 0.00621 -0.0658 0.0160 1.0000
7.500 1.1519 0.01324 0.00674 -0.0647 0.0138 1.0000
7.750 1.1717 0.01390 0.00750 -0.0633 0.0122 1.0000
8.000 1.1933 0.01435 0.00800 -0.0623 0.0116 1.0000
8.250 1.2138 0.01488 0.00859 -0.0611 0.0108 1.0000
8.500 1.2335 0.01545 0.00922 -0.0598 0.0102 1.0000
8.750 1.2520 0.01611 0.00993 -0.0584 0.0096 1.0000
9.000 1.2626 0.01741 0.01135 -0.0557 0.0087 1.0000
9.250 1.2784 0.01821 0.01225 -0.0538 0.0084 1.0000
9.500 1.2972 0.01872 0.01282 -0.0525 0.0080 1.0000
9.750 1.3122 0.01950 0.01367 -0.0506 0.0077 1.0000
10.000 1.3260 0.02033 0.01458 -0.0485 0.0074 1.0000
10.250 1.3381 0.02114 0.01547 -0.0461 0.0071 1.0000
10.500 1.3456 0.02208 0.01650 -0.0430 0.0069 1.0000
10.750 1.3551 0.02292 0.01740 -0.0404 0.0067 1.0000
11.000 1.3617 0.02401 0.01859 -0.0376 0.0066 1.0000
11.250 1.3695 0.02505 0.01970 -0.0351 0.0063 1.0000
11.500 1.3719 0.02660 0.02134 -0.0323 0.0061 1.0000
11.750 1.3725 0.02846 0.02332 -0.0296 0.0060 1.0000
12.000 1.3614 0.03192 0.02702 -0.0260 0.0057 1.0000
12.250 1.3653 0.03369 0.02892 -0.0242 0.0056 1.0000
12.500 1.3734 0.03489 0.03022 -0.0230 0.0055 1.0000
12.750 1.3762 0.03687 0.03233 -0.0216 0.0054 1.0000
13.000 1.3804 0.03870 0.03428 -0.0207 0.0053 1.0000
13.250 1.3830 0.04081 0.03651 -0.0198 0.0050 1.0000
13.500 1.3795 0.04378 0.03964 -0.0190 0.0050 1.0000
13.750 1.3752 0.04694 0.04297 -0.0185 0.0049 1.0000
14.000 1.3691 0.05047 0.04666 -0.0183 0.0049 1.0000
14.250 1.3639 0.05397 0.05029 -0.0186 0.0048 1.0000
14.500 1.3507 0.05877 0.05529 -0.0192 0.0047 1.0000
14.750 1.3429 0.06298 0.05964 -0.0202 0.0047 1.0000
15.000 1.3282 0.06852 0.06535 -0.0219 0.0047 1.0000
15.250 1.3151 0.07412 0.07111 -0.0240 0.0046 1.0000
15.500 1.3005 0.08027 0.07742 -0.0266 0.0046 1.0000
15.750 1.2777 0.08836 0.08571 -0.0304 0.0047 1.0000
16.000 1.2546 0.09691 0.09445 -0.0347 0.0048 1.0000
16.250 1.2419 0.10378 0.10143 -0.0384 0.0047 1.0000
16.500 1.2155 0.11399 0.11182 -0.0441 0.0047 1.0000
16.750 1.2006 0.12201 0.11995 -0.0487 0.0047 1.0000
17.000 1.1638 0.13617 0.13430 -0.0569 0.0049 1.0000
17.250 1.1389 0.14824 0.14650 -0.0640 0.0050 1.0000
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Polar data table (+)
Polar graphs
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