BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Reynolds number: 100,000 Max Cl/Cd: 52.97 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69h083-il-100000.txt Download as CSV file: xf-fx69h083-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BELL/WORTMANN FX 69-H-083 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4890 0.09247 0.08805 -0.0112 1.0000 0.0741
-7.750 -0.4910 0.08857 0.08421 -0.0179 1.0000 0.0765
-7.500 -0.4925 0.08500 0.08050 -0.0291 1.0000 0.0780
-7.250 -0.4831 0.07918 0.07482 -0.0269 1.0000 0.0798
-7.000 -0.4719 0.07571 0.07139 -0.0251 1.0000 0.0834
-6.750 -0.4632 0.07185 0.06747 -0.0285 1.0000 0.0887
-6.500 -0.4575 0.06741 0.06283 -0.0338 1.0000 0.0931
-6.250 -0.4457 0.06421 0.05976 -0.0314 1.0000 0.0997
-6.000 -0.4405 0.06058 0.05594 -0.0336 1.0000 0.1075
-5.750 -0.4219 0.04800 0.04395 -0.0267 1.0000 0.1169
-5.500 -0.4279 0.04489 0.04075 -0.0252 1.0000 0.1217
-5.250 -0.4254 0.04246 0.03835 -0.0226 1.0000 0.1283
-5.000 -0.4234 0.05028 0.04549 -0.0261 1.0000 0.1404
-4.750 -0.4178 0.04781 0.04292 -0.0244 1.0000 0.1525
-4.500 -0.4103 0.04546 0.04046 -0.0227 1.0000 0.1670
-4.250 -0.4021 0.04349 0.03829 -0.0214 1.0000 0.1907
-4.000 -0.3919 0.04101 0.03587 -0.0194 1.0000 0.2086
-3.750 -0.3815 0.03894 0.03379 -0.0176 1.0000 0.2377
-3.500 -0.3255 0.03163 0.02435 -0.0193 1.0000 0.0933
-3.250 -0.2995 0.02930 0.02128 -0.0177 1.0000 0.0786
-3.000 -0.2751 0.02634 0.01815 -0.0173 1.0000 0.0746
-2.750 -0.2431 0.02401 0.01535 -0.0176 0.9987 0.0701
-2.500 -0.1976 0.02201 0.01291 -0.0203 0.9940 0.0696
-2.250 -0.1545 0.02094 0.01154 -0.0231 0.9873 0.0775
-2.000 -0.1097 0.01929 0.00995 -0.0263 0.9826 0.0836
-1.750 -0.0709 0.01822 0.00892 -0.0285 0.9749 0.0967
-1.500 -0.0046 0.01426 0.00799 -0.0341 0.9803 1.0000
-1.250 0.0432 0.01444 0.00773 -0.0385 0.9716 1.0000
-1.000 0.0895 0.01462 0.00762 -0.0427 0.9624 1.0000
-0.750 0.1450 0.01473 0.00749 -0.0487 0.9558 1.0000
-0.500 0.1897 0.01484 0.00741 -0.0524 0.9450 1.0000
-0.250 0.2328 0.01493 0.00738 -0.0557 0.9341 1.0000
0.000 0.2729 0.01503 0.00738 -0.0582 0.9229 1.0000
0.250 0.3091 0.01512 0.00740 -0.0598 0.9115 1.0000
0.500 0.3416 0.01522 0.00744 -0.0605 0.8999 1.0000
0.750 0.3699 0.01534 0.00751 -0.0603 0.8878 1.0000
1.000 0.3943 0.01548 0.00763 -0.0594 0.8746 1.0000
1.250 0.4177 0.01562 0.00776 -0.0582 0.8614 1.0000
1.500 0.4405 0.01575 0.00788 -0.0569 0.8483 1.0000
1.750 0.4630 0.01587 0.00799 -0.0554 0.8351 1.0000
2.000 0.4854 0.01595 0.00807 -0.0539 0.8218 1.0000
2.250 0.5075 0.01597 0.00810 -0.0521 0.8079 1.0000
2.500 0.5295 0.01594 0.00812 -0.0503 0.7937 1.0000
2.750 0.5517 0.01590 0.00809 -0.0484 0.7793 1.0000
3.000 0.5742 0.01586 0.00808 -0.0466 0.7649 1.0000
3.250 0.5971 0.01584 0.00808 -0.0450 0.7504 1.0000
3.500 0.6200 0.01584 0.00816 -0.0434 0.7349 1.0000
3.750 0.6429 0.01587 0.00827 -0.0420 0.7174 1.0000
4.000 0.6663 0.01586 0.00831 -0.0405 0.7002 1.0000
4.250 0.6901 0.01583 0.00833 -0.0390 0.6833 1.0000
4.500 0.7142 0.01586 0.00842 -0.0376 0.6659 1.0000
4.750 0.7378 0.01595 0.00867 -0.0364 0.6455 1.0000
5.000 0.7621 0.01597 0.00873 -0.0350 0.6262 1.0000
5.250 0.7857 0.01611 0.00900 -0.0338 0.6035 1.0000
5.500 0.8094 0.01620 0.00921 -0.0325 0.5797 1.0000
5.750 0.8313 0.01612 0.00914 -0.0305 0.5438 1.0000
6.000 0.8486 0.01602 0.00894 -0.0278 0.4712 1.0000
6.250 0.8641 0.01662 0.00919 -0.0254 0.3698 1.0000
6.500 0.8576 0.02072 0.01121 -0.0214 0.0964 1.0000
6.750 0.8666 0.02323 0.01356 -0.0186 0.0672 1.0000
7.000 0.8817 0.02484 0.01515 -0.0167 0.0552 1.0000
7.250 0.8989 0.02648 0.01681 -0.0150 0.0495 1.0000
7.500 0.9192 0.02919 0.01936 -0.0136 0.0462 1.0000
7.750 0.9451 0.03150 0.02187 -0.0126 0.0448 1.0000
8.000 0.9697 0.03398 0.02471 -0.0115 0.0430 1.0000
8.250 0.9907 0.03639 0.02744 -0.0103 0.0403 1.0000
8.500 1.0099 0.03958 0.03105 -0.0089 0.0400 1.0000
8.750 1.0249 0.04348 0.03548 -0.0070 0.0412 1.0000
9.000 1.0355 0.04769 0.04016 -0.0051 0.0429 1.0000
9.250 1.0432 0.05233 0.04516 -0.0034 0.0446 1.0000
9.500 1.0475 0.05639 0.04982 -0.0009 0.0490 1.0000
9.750 1.0360 0.06228 0.05629 0.0016 0.0544 1.0000
10.000 0.9492 0.05547 0.04998 0.0108 0.0525 1.0000
10.250 0.9280 0.05965 0.05436 0.0132 0.0539 1.0000
10.500 0.9067 0.06404 0.05890 0.0145 0.0548 1.0000
11.250 0.8251 0.07956 0.07484 0.0122 0.0549 1.0000
11.500 0.7927 0.08650 0.08188 0.0086 0.0543 1.0000
11.750 0.7619 0.09445 0.08990 0.0041 0.0541 1.0000
12.000 0.7371 0.10263 0.09811 -0.0002 0.0550 1.0000
12.250 0.7091 0.11369 0.10911 -0.0063 0.0608 1.0000
12.500 0.6809 0.13546 0.13085 -0.0154 0.1340 1.0000
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Polar data table (+)
Polar graphs
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