BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Reynolds number: 200,000 Max Cl/Cd: 66.22 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx69h083-il-200000-n5.txt Download as CSV file: xf-fx69h083-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3925 0.06377 0.06090 -0.0257 1.0000 0.0176
-7.250 -0.3982 0.05895 0.05610 -0.0290 1.0000 0.0166
-6.750 -0.4373 0.06409 0.06077 -0.0343 1.0000 0.0204
-6.250 -0.4126 0.04916 0.04545 -0.0401 0.9763 0.0114
-6.000 -0.3917 0.04362 0.03962 -0.0424 0.9648 0.0113
-5.500 -0.3502 0.03381 0.02902 -0.0435 0.9444 0.0113
-5.250 -0.3294 0.02977 0.02449 -0.0427 0.9351 0.0116
-5.000 -0.3103 0.02566 0.01978 -0.0416 0.9268 0.0126
-4.750 -0.2881 0.02472 0.01870 -0.0413 0.9180 0.0145
-4.500 -0.2646 0.02256 0.01613 -0.0403 0.9103 0.0156
-4.250 -0.2405 0.02034 0.01341 -0.0391 0.9027 0.0164
-4.000 -0.2153 0.01858 0.01128 -0.0381 0.8949 0.0176
-3.750 -0.1899 0.01760 0.01002 -0.0372 0.8878 0.0198
-3.500 -0.1648 0.01616 0.00835 -0.0365 0.8798 0.0220
-3.250 -0.1405 0.01506 0.00713 -0.0355 0.8727 0.0237
-3.000 -0.1153 0.01432 0.00632 -0.0349 0.8639 0.0257
-2.750 -0.0900 0.01386 0.00576 -0.0343 0.8560 0.0293
-2.500 -0.0649 0.01326 0.00502 -0.0336 0.8478 0.0305
-2.250 -0.0392 0.01279 0.00443 -0.0330 0.8394 0.0318
-2.000 -0.0139 0.01233 0.00385 -0.0323 0.8319 0.0355
-1.750 0.0124 0.01195 0.00346 -0.0319 0.8229 0.0479
-1.500 0.0376 0.01145 0.00316 -0.0315 0.8148 0.1099
-1.250 0.0603 0.01055 0.00292 -0.0309 0.8058 0.3075
-1.000 0.1044 0.00875 0.00321 -0.0328 0.7974 0.9710
-0.750 0.1670 0.00876 0.00299 -0.0401 0.7865 1.0000
-0.500 0.1922 0.00874 0.00280 -0.0396 0.7750 1.0000
-0.250 0.2178 0.00874 0.00267 -0.0391 0.7635 1.0000
0.000 0.2435 0.00874 0.00256 -0.0388 0.7519 1.0000
0.250 0.2693 0.00876 0.00247 -0.0384 0.7409 1.0000
0.500 0.2950 0.00878 0.00240 -0.0380 0.7302 1.0000
0.750 0.3207 0.00882 0.00235 -0.0376 0.7192 1.0000
1.000 0.3464 0.00886 0.00231 -0.0372 0.7073 1.0000
1.250 0.3721 0.00891 0.00230 -0.0368 0.6941 1.0000
1.500 0.3976 0.00897 0.00228 -0.0363 0.6791 1.0000
1.750 0.4231 0.00904 0.00227 -0.0358 0.6602 1.0000
2.000 0.4483 0.00914 0.00227 -0.0353 0.6401 1.0000
2.250 0.4737 0.00924 0.00232 -0.0348 0.6212 1.0000
2.500 0.4992 0.00936 0.00238 -0.0344 0.6044 1.0000
2.750 0.5248 0.00949 0.00248 -0.0341 0.5898 1.0000
3.000 0.5504 0.00962 0.00259 -0.0337 0.5750 1.0000
3.250 0.5758 0.00978 0.00275 -0.0333 0.5588 1.0000
3.500 0.6011 0.00995 0.00290 -0.0328 0.5415 1.0000
3.750 0.6263 0.01013 0.00307 -0.0324 0.5214 1.0000
4.000 0.6513 0.01034 0.00325 -0.0320 0.4996 1.0000
4.250 0.6763 0.01056 0.00346 -0.0315 0.4786 1.0000
4.500 0.7012 0.01080 0.00374 -0.0311 0.4584 1.0000
4.750 0.7262 0.01105 0.00402 -0.0307 0.4397 1.0000
5.000 0.7509 0.01134 0.00432 -0.0302 0.4169 1.0000
5.250 0.7745 0.01174 0.00466 -0.0296 0.3802 1.0000
5.500 0.7948 0.01253 0.00508 -0.0288 0.2981 1.0000
5.750 0.8093 0.01419 0.00587 -0.0276 0.1519 1.0000
6.000 0.8282 0.01534 0.00673 -0.0267 0.0853 1.0000
6.250 0.8463 0.01659 0.00767 -0.0257 0.0289 1.0000
6.500 0.8666 0.01756 0.00868 -0.0247 0.0183 1.0000
6.750 0.8874 0.01842 0.00970 -0.0237 0.0154 1.0000
7.000 0.9054 0.01962 0.01101 -0.0224 0.0122 1.0000
7.250 0.9232 0.02079 0.01234 -0.0211 0.0111 1.0000
7.500 0.9405 0.02200 0.01371 -0.0197 0.0104 1.0000
7.750 0.9568 0.02339 0.01524 -0.0182 0.0099 1.0000
8.000 0.9729 0.02493 0.01692 -0.0167 0.0094 1.0000
8.250 0.9894 0.02665 0.01886 -0.0152 0.0090 1.0000
8.500 1.0067 0.02846 0.02085 -0.0138 0.0086 1.0000
8.750 1.0236 0.02998 0.02253 -0.0127 0.0078 1.0000
9.000 1.0385 0.03149 0.02417 -0.0115 0.0070 1.0000
9.250 1.0498 0.03424 0.02714 -0.0100 0.0064 1.0000
9.500 1.0577 0.03789 0.03116 -0.0081 0.0062 1.0000
9.750 1.0633 0.04095 0.03455 -0.0061 0.0061 1.0000
10.000 1.0661 0.04365 0.03759 -0.0040 0.0060 1.0000
10.250 1.0627 0.04641 0.04064 -0.0014 0.0060 1.0000
10.500 1.0558 0.04942 0.04395 0.0008 0.0060 1.0000
10.750 1.0462 0.05277 0.04756 0.0024 0.0060 1.0000
11.000 1.0346 0.05649 0.05154 0.0032 0.0060 1.0000
11.250 1.0213 0.06067 0.05595 0.0031 0.0060 1.0000
11.500 1.0067 0.06537 0.06086 0.0021 0.0060 1.0000
11.750 0.9911 0.07065 0.06634 0.0002 0.0060 1.0000
12.000 0.9747 0.07656 0.07244 -0.0027 0.0060 1.0000
12.250 0.9579 0.08314 0.07918 -0.0064 0.0060 1.0000
12.500 0.9407 0.09047 0.08665 -0.0109 0.0061 1.0000
12.750 0.9235 0.09848 0.09478 -0.0158 0.0061 1.0000
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Polar data table (+)
Polar graphs
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