BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.6 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx69h083-il-1000000-n5.txt Download as CSV file: xf-fx69h083-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5345 0.08991 0.08838 0.0012 0.9241 0.0022
-8.250 -0.5363 0.08532 0.08376 -0.0018 0.9111 0.0022
-8.000 -0.5390 0.08032 0.07872 -0.0066 0.8985 0.0022
-7.750 -0.5353 0.07449 0.07284 -0.0127 0.8883 0.0022
-7.500 -0.5286 0.06833 0.06661 -0.0184 0.8795 0.0023
-7.250 -0.5198 0.06206 0.06023 -0.0231 0.8715 0.0024
-7.000 -0.5090 0.05537 0.05339 -0.0269 0.8635 0.0025
-6.750 -0.4973 0.04804 0.04584 -0.0296 0.8562 0.0027
-6.500 -0.5237 0.01692 0.01263 -0.0264 0.8486 0.0031
-6.250 -0.5003 0.01504 0.01038 -0.0257 0.8425 0.0032
-6.000 -0.4747 0.01413 0.00928 -0.0254 0.8357 0.0034
-5.750 -0.4487 0.01340 0.00835 -0.0252 0.8296 0.0035
-5.500 -0.4247 0.01169 0.00630 -0.0245 0.8226 0.0041
-5.250 -0.3979 0.01123 0.00576 -0.0243 0.8159 0.0046
-5.000 -0.3708 0.01089 0.00534 -0.0242 0.8079 0.0050
-4.750 -0.3437 0.01054 0.00492 -0.0241 0.7997 0.0056
-4.500 -0.3168 0.01017 0.00444 -0.0240 0.7907 0.0062
-4.250 -0.2894 0.00990 0.00408 -0.0239 0.7798 0.0066
-4.000 -0.2625 0.00953 0.00365 -0.0238 0.7680 0.0078
-3.750 -0.2346 0.00949 0.00357 -0.0239 0.7568 0.0091
-3.500 -0.2068 0.00935 0.00339 -0.0239 0.7478 0.0105
-3.250 -0.1790 0.00922 0.00320 -0.0240 0.7377 0.0114
-3.000 -0.1511 0.00913 0.00306 -0.0241 0.7248 0.0118
-2.750 -0.1244 0.00866 0.00244 -0.0239 0.7109 0.0133
-2.500 -0.0969 0.00842 0.00211 -0.0238 0.6976 0.0147
-2.250 -0.0691 0.00824 0.00184 -0.0238 0.6863 0.0152
-2.000 -0.0412 0.00810 0.00163 -0.0239 0.6747 0.0160
-1.750 -0.0132 0.00798 0.00144 -0.0239 0.6623 0.0165
-1.500 0.0148 0.00789 0.00127 -0.0240 0.6482 0.0170
-1.250 0.0428 0.00783 0.00112 -0.0241 0.6322 0.0180
-1.000 0.0709 0.00779 0.00101 -0.0242 0.6168 0.0204
-0.750 0.0986 0.00770 0.00093 -0.0243 0.5983 0.0428
-0.500 0.1262 0.00760 0.00087 -0.0244 0.5786 0.0811
-0.250 0.1535 0.00743 0.00082 -0.0245 0.5602 0.1500
0.000 0.1804 0.00714 0.00079 -0.0246 0.5438 0.2613
0.250 0.2070 0.00684 0.00077 -0.0247 0.5266 0.3854
0.750 0.2454 0.00532 0.00089 -0.0210 0.4876 0.9529
1.000 0.2816 0.00549 0.00098 -0.0228 0.4664 0.9816
1.250 0.3208 0.00565 0.00104 -0.0254 0.4468 0.9889
1.500 0.3569 0.00580 0.00110 -0.0274 0.4277 0.9918
1.750 0.3899 0.00597 0.00115 -0.0288 0.4032 0.9944
2.000 0.4233 0.00616 0.00122 -0.0303 0.3761 0.9959
2.250 0.4563 0.00632 0.00128 -0.0316 0.3553 0.9973
2.500 0.4886 0.00646 0.00137 -0.0328 0.3394 0.9986
2.750 0.5198 0.00665 0.00146 -0.0339 0.3168 0.9997
3.000 0.5475 0.00682 0.00155 -0.0341 0.2947 1.0000
3.250 0.5728 0.00702 0.00168 -0.0338 0.2712 1.0000
3.500 0.5977 0.00734 0.00184 -0.0335 0.2362 1.0000
3.750 0.6220 0.00772 0.00204 -0.0331 0.1904 1.0000
4.000 0.6462 0.00810 0.00225 -0.0327 0.1538 1.0000
4.250 0.6713 0.00827 0.00241 -0.0323 0.1473 1.0000
4.500 0.6958 0.00856 0.00266 -0.0319 0.1271 1.0000
4.750 0.7191 0.00906 0.00295 -0.0314 0.0815 1.0000
5.000 0.7440 0.00927 0.00316 -0.0310 0.0730 1.0000
5.250 0.7674 0.00974 0.00346 -0.0305 0.0409 1.0000
5.500 0.7904 0.01028 0.00387 -0.0298 0.0142 1.0000
5.750 0.8146 0.01062 0.00419 -0.0294 0.0085 1.0000
6.000 0.8390 0.01097 0.00461 -0.0289 0.0061 1.0000
6.250 0.8637 0.01128 0.00496 -0.0285 0.0055 1.0000
6.500 0.8881 0.01164 0.00536 -0.0281 0.0049 1.0000
6.750 0.9124 0.01203 0.00579 -0.0277 0.0042 1.0000
7.000 0.9359 0.01255 0.00635 -0.0272 0.0035 1.0000
7.250 0.9585 0.01322 0.00712 -0.0265 0.0031 1.0000
7.500 0.9821 0.01370 0.00766 -0.0260 0.0029 1.0000
7.750 1.0053 0.01425 0.00831 -0.0255 0.0028 1.0000
8.000 1.0279 0.01485 0.00898 -0.0250 0.0026 1.0000
8.250 1.0499 0.01551 0.00972 -0.0243 0.0024 1.0000
8.500 1.0717 0.01619 0.01047 -0.0237 0.0022 1.0000
8.750 1.0930 0.01688 0.01123 -0.0230 0.0020 1.0000
9.000 1.1140 0.01759 0.01201 -0.0223 0.0019 1.0000
9.250 1.1340 0.01839 0.01288 -0.0215 0.0018 1.0000
9.500 1.1519 0.01942 0.01402 -0.0205 0.0017 1.0000
9.750 1.1654 0.02097 0.01573 -0.0188 0.0016 1.0000
10.000 1.1733 0.02325 0.01825 -0.0165 0.0015 1.0000
10.250 1.1825 0.02530 0.02054 -0.0145 0.0014 1.0000
10.500 1.1930 0.02702 0.02245 -0.0127 0.0014 1.0000
10.750 1.1989 0.02888 0.02452 -0.0104 0.0014 1.0000
11.000 1.2011 0.03091 0.02675 -0.0079 0.0014 1.0000
11.250 1.2020 0.03306 0.02909 -0.0057 0.0014 1.0000
11.500 1.2022 0.03528 0.03150 -0.0040 0.0014 1.0000
11.750 1.1996 0.03790 0.03432 -0.0025 0.0014 1.0000
12.000 1.1956 0.04079 0.03739 -0.0014 0.0014 1.0000
12.250 1.1880 0.04424 0.04105 -0.0008 0.0014 1.0000
12.500 1.1796 0.04802 0.04501 -0.0009 0.0013 1.0000
12.750 1.1704 0.05216 0.04933 -0.0016 0.0013 1.0000
13.000 1.1549 0.05752 0.05488 -0.0031 0.0013 1.0000
13.250 1.1399 0.06325 0.06079 -0.0055 0.0013 1.0000
13.500 1.1217 0.06996 0.06767 -0.0088 0.0013 1.0000
13.750 1.1016 0.07762 0.07549 -0.0129 0.0013 1.0000
14.000 1.0828 0.08564 0.08365 -0.0175 0.0013 1.0000
14.250 1.0573 0.09588 0.09404 -0.0235 0.0014 1.0000
14.500 1.0306 0.10713 0.10541 -0.0298 0.0014 1.0000
14.750 0.9927 0.12249 0.12091 -0.0377 0.0014 1.0000
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Polar data table (+)
Polar graphs
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