BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Reynolds number: 50,000 Max Cl/Cd: 27.63 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69h098-il-50000.txt Download as CSV file: xf-fx69h098-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BELL/WORTMANN FX 69-H-098 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5485 0.14334 0.13623 0.0068 1.0000 0.1867
-11.000 -0.5239 0.13707 0.12992 0.0085 1.0000 0.1956
-10.750 -0.5429 0.13649 0.12945 0.0053 1.0000 0.2015
-10.500 -0.5168 0.13030 0.12320 0.0071 1.0000 0.2112
-10.250 -0.5251 0.12777 0.12076 0.0052 1.0000 0.2178
-10.000 -0.5171 0.12429 0.11729 0.0054 1.0000 0.2291
-9.750 -0.5052 0.11992 0.11294 0.0058 1.0000 0.2379
-9.500 -0.5129 0.11733 0.11043 0.0044 1.0000 0.2473
-9.250 -0.5167 0.11498 0.10814 0.0038 1.0000 0.2596
-9.000 -0.5019 0.11063 0.10380 0.0048 1.0000 0.2728
-8.750 -0.4934 0.10691 0.10011 0.0053 1.0000 0.2860
-8.500 -0.4911 0.10381 0.09707 0.0056 1.0000 0.3015
-8.250 -0.4951 0.10124 0.09457 0.0058 1.0000 0.3181
-8.000 -0.4819 0.09726 0.09063 0.0072 1.0000 0.3372
-7.750 -0.4721 0.09409 0.08746 0.0086 1.0000 0.3594
-7.500 -0.4796 0.09170 0.08518 0.0095 1.0000 0.3796
-7.250 -0.4575 0.08764 0.08110 0.0112 1.0000 0.4018
-6.750 -0.4452 0.08161 0.07517 0.0145 1.0000 0.4487
-5.750 -0.5157 0.05296 0.04578 -0.0207 1.0000 0.1822
-5.500 -0.5031 0.04730 0.03944 -0.0208 1.0000 0.1510
-5.250 -0.4880 0.04322 0.03477 -0.0196 1.0000 0.1365
-5.000 -0.4710 0.03991 0.03069 -0.0178 1.0000 0.1268
-4.750 -0.4521 0.03693 0.02737 -0.0162 1.0000 0.1231
-4.500 -0.4314 0.03427 0.02425 -0.0146 1.0000 0.1200
-4.250 -0.4094 0.03203 0.02162 -0.0132 1.0000 0.1200
-4.000 -0.3867 0.03017 0.01944 -0.0118 1.0000 0.1238
-3.750 -0.3623 0.02851 0.01737 -0.0105 1.0000 0.1275
-3.500 -0.3362 0.02662 0.01538 -0.0096 1.0000 0.1317
-3.250 -0.3091 0.02510 0.01376 -0.0086 1.0000 0.1402
-3.000 -0.1071 0.01874 0.01066 -0.0312 1.0000 1.0000
-2.750 -0.1010 0.01837 0.01003 -0.0286 1.0000 1.0000
-2.500 -0.0936 0.01813 0.00954 -0.0258 1.0000 1.0000
-2.250 -0.0850 0.01797 0.00916 -0.0231 1.0000 1.0000
-2.000 -0.0756 0.01789 0.00886 -0.0204 1.0000 1.0000
-1.750 -0.0655 0.01786 0.00861 -0.0178 1.0000 1.0000
-1.500 -0.0548 0.01789 0.00845 -0.0153 1.0000 1.0000
-1.250 -0.0438 0.01797 0.00836 -0.0128 1.0000 1.0000
-1.000 -0.0325 0.01809 0.00833 -0.0105 1.0000 1.0000
-0.750 -0.0207 0.01827 0.00836 -0.0083 1.0000 1.0000
-0.500 -0.0085 0.01850 0.00845 -0.0062 1.0000 1.0000
-0.250 0.0042 0.01879 0.00862 -0.0044 1.0000 1.0000
0.000 0.0173 0.01915 0.00889 -0.0029 1.0000 1.0000
0.250 0.0303 0.01959 0.00925 -0.0015 1.0000 1.0000
0.500 0.0431 0.02014 0.00971 -0.0004 1.0000 1.0000
0.750 0.0553 0.02081 0.01034 0.0005 1.0000 1.0000
1.000 0.1143 0.02185 0.01134 -0.0076 0.9828 1.0000
1.250 0.1990 0.02257 0.01208 -0.0197 0.9482 1.0000
1.500 0.2888 0.02271 0.01231 -0.0315 0.9129 1.0000
1.750 0.3653 0.02229 0.01202 -0.0397 0.8733 1.0000
2.000 0.4256 0.02163 0.01146 -0.0438 0.8338 1.0000
2.250 0.4712 0.02106 0.01087 -0.0447 0.7954 1.0000
2.500 0.5005 0.02098 0.01071 -0.0432 0.7551 1.0000
2.750 0.5276 0.02105 0.01068 -0.0414 0.7197 1.0000
3.000 0.5512 0.02139 0.01092 -0.0396 0.6858 1.0000
3.250 0.5751 0.02180 0.01122 -0.0381 0.6563 1.0000
3.500 0.5991 0.02226 0.01159 -0.0366 0.6302 1.0000
3.750 0.6225 0.02285 0.01214 -0.0353 0.6059 1.0000
4.000 0.6455 0.02355 0.01281 -0.0341 0.5838 1.0000
4.250 0.6687 0.02429 0.01354 -0.0330 0.5634 1.0000
4.500 0.6925 0.02506 0.01428 -0.0319 0.5454 1.0000
4.750 0.7154 0.02594 0.01521 -0.0309 0.5283 1.0000
5.000 0.7374 0.02695 0.01630 -0.0300 0.5119 1.0000
5.250 0.7596 0.02800 0.01744 -0.0290 0.4971 1.0000
5.500 0.7818 0.02908 0.01861 -0.0281 0.4831 1.0000
5.750 0.8048 0.03016 0.01979 -0.0272 0.4702 1.0000
6.000 0.8245 0.03153 0.02137 -0.0263 0.4573 1.0000
6.250 0.8433 0.03302 0.02308 -0.0253 0.4448 1.0000
6.500 0.8616 0.03464 0.02492 -0.0243 0.4332 1.0000
6.750 0.8812 0.03615 0.02661 -0.0232 0.4217 1.0000
7.000 0.9027 0.03748 0.02810 -0.0221 0.4100 1.0000
7.250 0.9221 0.03891 0.02970 -0.0209 0.3970 1.0000
7.500 0.9394 0.04038 0.03138 -0.0194 0.3825 1.0000
7.750 0.9567 0.04163 0.03280 -0.0177 0.3657 1.0000
8.000 0.9693 0.04317 0.03460 -0.0157 0.3476 1.0000
8.250 0.9901 0.04355 0.03512 -0.0137 0.3259 1.0000
8.500 1.0072 0.04393 0.03563 -0.0113 0.3006 1.0000
8.750 1.0383 0.04160 0.03297 -0.0088 0.2635 1.0000
9.000 1.0508 0.04115 0.03255 -0.0054 0.2257 1.0000
9.250 1.0626 0.04109 0.03231 -0.0021 0.1882 1.0000
9.500 1.0721 0.04235 0.03346 0.0008 0.1608 1.0000
9.750 1.0832 0.04372 0.03470 0.0032 0.1405 1.0000
10.000 1.0915 0.04630 0.03742 0.0055 0.1278 1.0000
10.250 1.0941 0.04941 0.04083 0.0078 0.1189 1.0000
10.500 1.1034 0.05208 0.04352 0.0096 0.1109 1.0000
10.750 1.0939 0.05638 0.04833 0.0121 0.1083 1.0000
11.000 1.0807 0.06066 0.05298 0.0144 0.1065 1.0000
11.250 1.0588 0.06511 0.05772 0.0165 0.1062 1.0000
11.500 1.0274 0.07053 0.06337 0.0173 0.1077 1.0000
11.750 0.9953 0.07709 0.07009 0.0156 0.1096 1.0000
12.000 0.9657 0.08470 0.07777 0.0120 0.1112 1.0000
12.250 0.9405 0.09302 0.08612 0.0076 0.1124 1.0000
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