BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Reynolds number: 50,000 Max Cl/Cd: 36.32 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69h083-il-50000.txt Download as CSV file: xf-fx69h083-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4969 0.10319 0.09698 -0.0019 1.0000 0.2055
-8.000 -0.5028 0.10081 0.09469 -0.0043 1.0000 0.2160
-7.750 -0.4945 0.09677 0.09069 -0.0040 1.0000 0.2291
-7.500 -0.4906 0.09318 0.08717 -0.0042 1.0000 0.2427
-7.250 -0.4912 0.08998 0.08404 -0.0056 1.0000 0.2574
-7.000 -0.4878 0.08629 0.08043 -0.0060 1.0000 0.2739
-6.750 -0.4774 0.08275 0.07693 -0.0040 1.0000 0.2980
-6.500 -0.4740 0.07967 0.07392 -0.0028 1.0000 0.3268
-6.250 -0.4622 0.07635 0.07065 0.0017 1.0000 0.3668
-6.000 -0.4623 0.07396 0.06830 0.0050 1.0000 0.4117
-5.750 -0.4366 0.07027 0.06463 0.0126 1.0000 0.4721
-5.500 -0.4011 0.06672 0.06100 0.0198 1.0000 0.5609
-5.000 -0.2403 0.05435 0.04818 0.0207 1.0000 0.8484
-4.750 -0.2851 0.05422 0.04828 0.0245 1.0000 0.7775
-4.500 -0.3467 0.05374 0.04819 0.0256 1.0000 0.6812
-4.250 -0.3904 0.04563 0.03856 -0.0233 1.0000 0.2301
-4.000 -0.3573 0.04039 0.03241 -0.0249 1.0000 0.1563
-3.750 -0.3323 0.03724 0.02834 -0.0240 1.0000 0.1323
-3.500 -0.3113 0.03429 0.02509 -0.0230 1.0000 0.1254
-3.250 -0.2890 0.03208 0.02242 -0.0220 1.0000 0.1252
-3.000 -0.2655 0.03011 0.02004 -0.0211 1.0000 0.1268
-2.750 -0.2399 0.02821 0.01772 -0.0202 1.0000 0.1258
-2.500 -0.2137 0.02659 0.01574 -0.0194 1.0000 0.1276
-2.250 -0.1865 0.02527 0.01402 -0.0187 1.0000 0.1325
-2.000 -0.1588 0.02400 0.01274 -0.0184 1.0000 0.1501
-1.750 -0.1309 0.02288 0.01156 -0.0180 1.0000 0.1740
-1.500 -0.0694 0.01811 0.00953 -0.0213 1.0000 1.0000
-1.250 -0.0539 0.01836 0.00929 -0.0197 1.0000 1.0000
-1.000 -0.0380 0.01865 0.00917 -0.0184 1.0000 1.0000
-0.750 -0.0215 0.01898 0.00920 -0.0173 1.0000 1.0000
-0.500 -0.0046 0.01934 0.00930 -0.0164 1.0000 1.0000
-0.250 0.0126 0.01976 0.00949 -0.0157 1.0000 1.0000
0.000 0.0299 0.02022 0.00974 -0.0151 1.0000 1.0000
0.250 0.0474 0.02072 0.01007 -0.0146 1.0000 1.0000
0.500 0.0650 0.02128 0.01044 -0.0142 1.0000 1.0000
0.750 0.0826 0.02189 0.01092 -0.0140 1.0000 1.0000
1.000 0.1104 0.02266 0.01157 -0.0158 0.9960 1.0000
1.250 0.1651 0.02376 0.01254 -0.0226 0.9816 1.0000
1.500 0.2134 0.02475 0.01345 -0.0280 0.9659 1.0000
1.750 0.2590 0.02571 0.01438 -0.0328 0.9499 1.0000
2.000 0.3034 0.02664 0.01532 -0.0372 0.9336 1.0000
2.250 0.3479 0.02755 0.01628 -0.0414 0.9173 1.0000
2.500 0.3936 0.02841 0.01722 -0.0456 0.9013 1.0000
2.750 0.4241 0.02923 0.01812 -0.0470 0.8832 1.0000
3.000 0.4609 0.03001 0.01901 -0.0493 0.8654 1.0000
3.250 0.5040 0.03067 0.01988 -0.0523 0.8482 1.0000
3.500 0.5403 0.03132 0.02069 -0.0541 0.8303 1.0000
3.750 0.5682 0.03204 0.02156 -0.0543 0.8116 1.0000
4.000 0.6021 0.03259 0.02237 -0.0552 0.7945 1.0000
4.250 0.6362 0.03307 0.02307 -0.0558 0.7783 1.0000
4.500 0.6597 0.03379 0.02399 -0.0551 0.7599 1.0000
4.750 0.6869 0.03423 0.02466 -0.0543 0.7409 1.0000
5.000 0.7234 0.03394 0.02468 -0.0536 0.7230 1.0000
5.250 0.7459 0.03418 0.02524 -0.0516 0.7007 1.0000
5.500 0.7833 0.03296 0.02436 -0.0493 0.6799 1.0000
5.750 0.8148 0.03155 0.02328 -0.0457 0.6541 1.0000
6.000 0.8435 0.03026 0.02232 -0.0420 0.6267 1.0000
6.250 0.8687 0.02899 0.02146 -0.0378 0.5931 1.0000
6.500 0.8895 0.02491 0.01730 -0.0287 0.5152 1.0000
6.750 0.8854 0.02438 0.01604 -0.0204 0.3461 1.0000
7.000 0.8715 0.02866 0.01826 -0.0149 0.1684 1.0000
7.250 0.8826 0.03206 0.02113 -0.0121 0.1247 1.0000
7.500 0.9062 0.03454 0.02351 -0.0105 0.1030 1.0000
7.750 0.9400 0.03768 0.02663 -0.0098 0.0933 1.0000
8.000 0.9674 0.04075 0.02988 -0.0090 0.0858 1.0000
8.250 0.9888 0.04434 0.03390 -0.0079 0.0809 1.0000
8.500 1.0066 0.04797 0.03809 -0.0063 0.0795 1.0000
8.750 1.0206 0.05206 0.04269 -0.0047 0.0798 1.0000
9.000 1.0307 0.05645 0.04753 -0.0032 0.0807 1.0000
9.250 1.0390 0.06122 0.05265 -0.0018 0.0820 1.0000
9.500 1.0444 0.06575 0.05758 -0.0003 0.0840 1.0000
9.750 1.0204 0.06979 0.06240 0.0021 0.0873 1.0000
10.000 1.0002 0.07457 0.06753 0.0032 0.0897 1.0000
10.250 0.9795 0.07912 0.07226 0.0040 0.0915 1.0000
10.500 0.9602 0.08405 0.07731 0.0036 0.0931 1.0000
10.750 0.9646 0.08967 0.08299 0.0034 0.0969 1.0000
11.000 0.9242 0.09578 0.08921 -0.0009 0.0976 1.0000
11.250 0.8729 0.10734 0.10076 -0.0119 0.1004 1.0000
11.500 0.8573 0.11687 0.11015 -0.0177 0.1062 1.0000
11.750 0.8371 0.12745 0.12062 -0.0252 0.1169 1.0000
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Polar data table (+)
Polar graphs
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