WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Reynolds number: 100,000 Max Cl/Cd: 6.06 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx6617ai-il-100000.txt Download as CSV file: xf-fx6617ai-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT N
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3049 0.10195 0.09727 -0.0650 0.7839 0.1785
-10.000 -0.3478 0.05644 0.05163 -0.0938 0.7741 0.0881
-9.750 -0.3555 0.05142 0.04649 -0.0947 0.7692 0.0855
-9.500 -0.4405 0.05870 0.05340 -0.0950 0.7756 0.0849
-9.250 -0.4696 0.05271 0.04651 -0.0958 0.7706 0.0750
-9.000 -0.4618 0.04908 0.04259 -0.0958 0.7647 0.0740
-8.750 -0.4523 0.04591 0.03908 -0.0956 0.7582 0.0734
-8.500 -0.4398 0.04293 0.03569 -0.0952 0.7530 0.0726
-8.250 -0.4240 0.04008 0.03244 -0.0949 0.7478 0.0713
-8.000 -0.4052 0.03759 0.02956 -0.0945 0.7424 0.0704
-7.750 -0.3840 0.03548 0.02707 -0.0939 0.7378 0.0703
-7.500 -0.3608 0.03373 0.02502 -0.0935 0.7332 0.0709
-7.250 -0.3362 0.03223 0.02332 -0.0932 0.7277 0.0721
-7.000 -0.3112 0.03110 0.02193 -0.0927 0.7231 0.0748
-6.750 -0.2859 0.02973 0.02044 -0.0922 0.7194 0.0780
-6.500 -0.2615 0.02869 0.01954 -0.0920 0.7147 0.0818
-6.250 -0.2374 0.02788 0.01873 -0.0914 0.7106 0.0863
-6.000 -0.2153 0.02699 0.01787 -0.0905 0.7071 0.0927
-5.750 -0.1935 0.02635 0.01720 -0.0896 0.7040 0.1039
-5.500 -0.1765 0.02550 0.01659 -0.0889 0.6996 0.1209
-5.250 -0.1662 0.02346 0.01541 -0.0881 0.6957 0.2171
-5.000 -0.1558 0.02302 0.01637 -0.0851 0.6923 0.5064
-4.750 -0.1307 0.02433 0.01753 -0.0832 0.6893 0.5521
-4.500 -0.1070 0.02572 0.01885 -0.0813 0.6862 0.5795
-4.250 -0.0852 0.02737 0.02055 -0.0786 0.6824 0.6012
-4.000 -0.0640 0.02912 0.02232 -0.0750 0.6789 0.6238
-3.750 -0.0422 0.03013 0.02320 -0.0725 0.6758 0.6455
-3.500 -0.0190 0.03083 0.02377 -0.0702 0.6732 0.6611
-3.250 0.0004 0.03171 0.02465 -0.0676 0.6700 0.6705
-3.000 0.0188 0.03219 0.02510 -0.0667 0.6666 0.6814
-2.750 0.0398 0.03241 0.02519 -0.0671 0.6635 0.6931
-2.500 0.0609 0.03271 0.02544 -0.0655 0.6608 0.6995
-2.250 0.0860 0.03263 0.02518 -0.0659 0.6583 0.7098
-2.000 0.1106 0.03273 0.02516 -0.0647 0.6563 0.7170
-1.750 0.1199 0.03381 0.02631 -0.0644 0.6518 0.7265
-1.500 0.1331 0.03467 0.02719 -0.0633 0.6487 0.7342
-1.250 0.1519 0.03520 0.02764 -0.0635 0.6460 0.7425
-1.000 0.1738 0.03545 0.02782 -0.0630 0.6436 0.7491
-0.750 0.2030 0.03538 0.02760 -0.0640 0.6416 0.7566
-0.500 0.2056 0.03710 0.02940 -0.0628 0.6378 0.7620
-0.250 0.1947 0.04017 0.03257 -0.0626 0.6343 0.7689
0.000 0.1935 0.04224 0.03466 -0.0619 0.6312 0.7744
0.250 0.1978 0.04397 0.03640 -0.0614 0.6292 0.7804
0.500 0.1749 0.04775 0.04022 -0.0608 0.6313 0.7870
0.750 0.1743 0.04991 0.04240 -0.0600 0.6327 0.7924
1.000 0.1856 0.05193 0.04440 -0.0609 0.6368 0.7986
1.250 0.2115 0.05329 0.04571 -0.0624 0.6414 0.8048
1.500 0.2382 0.05434 0.04672 -0.0630 0.6404 0.8113
1.750 0.1364 0.06175 0.05443 -0.0609 0.6949 0.8159
2.000 0.1667 0.06285 0.05547 -0.0619 0.6906 0.8220
2.250 0.2052 0.06466 0.05722 -0.0642 0.6885 0.8292
2.500 0.1949 0.06482 0.05739 -0.0613 0.6771 0.8353
2.750 0.2266 0.06620 0.05873 -0.0625 0.6740 0.8426
3.000 0.2612 0.06827 0.06076 -0.0646 0.6719 0.8499
3.250 0.2532 0.06817 0.06069 -0.0616 0.6597 0.8567
3.500 0.2885 0.06995 0.06242 -0.0635 0.6574 0.8652
3.750 0.2785 0.07053 0.06304 -0.0608 0.6470 0.8726
4.000 0.3089 0.07190 0.06440 -0.0620 0.6430 0.8818
4.250 0.3457 0.07387 0.06636 -0.0637 0.6410 0.8923
4.500 0.3294 0.07420 0.06675 -0.0606 0.6298 0.9023
4.750 0.3592 0.07568 0.06826 -0.0615 0.6266 0.9163
5.000 0.3981 0.07792 0.07056 -0.0635 0.6249 0.9362
5.250 0.3828 0.07806 0.07078 -0.0615 0.6124 1.0002
5.500 0.4227 0.08042 0.07311 -0.0649 0.6099 1.0002
5.750 0.4149 0.08181 0.07451 -0.0643 0.6003 1.0002
6.000 0.4479 0.08373 0.07640 -0.0667 0.5958 1.0002
6.250 0.4894 0.08635 0.07901 -0.0699 0.5937 1.0002
6.500 0.4729 0.08755 0.08022 -0.0685 0.5832 1.0002
6.750 0.5047 0.08964 0.08229 -0.0706 0.5796 1.0002
7.000 0.5454 0.09244 0.08509 -0.0733 0.5777 1.0002
7.250 0.5248 0.09348 0.08614 -0.0714 0.5665 1.0002
7.500 0.5554 0.09570 0.08836 -0.0731 0.5634 1.0002
7.750 0.5935 0.09866 0.09133 -0.0754 0.5618 1.0002
8.000 0.5690 0.09962 0.09230 -0.0733 0.5505 1.0002
8.250 0.5999 0.10191 0.09462 -0.0747 0.5475 1.0002
8.500 0.6371 0.10506 0.09779 -0.0767 0.5459 1.0002
8.750 0.6082 0.10597 0.09872 -0.0744 0.5348 1.0002
9.000 0.6393 0.10832 0.10110 -0.0756 0.5317 1.0002
9.250 0.6772 0.11168 0.10451 -0.0775 0.5302 1.0002
9.500 0.6457 0.11245 0.10531 -0.0753 0.5190 1.0002
9.750 0.6777 0.11495 0.10786 -0.0764 0.5160 1.0002
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Polar data table (+)
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