BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Reynolds number: 500,000 Max Cl/Cd: 90.08 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69h083-il-500000.txt Download as CSV file: xf-fx69h083-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5167 0.10589 0.10382 0.0026 1.0000 0.0107
-9.000 -0.5249 0.09924 0.09723 0.0005 1.0000 0.0112
-8.750 -0.5216 0.09563 0.09363 -0.0008 1.0000 0.0114
-8.500 -0.5171 0.09222 0.09024 -0.0022 1.0000 0.0117
-8.250 -0.5132 0.08857 0.08659 -0.0045 1.0000 0.0120
-8.000 -0.5102 0.08454 0.08258 -0.0078 1.0000 0.0123
-7.750 -0.5073 0.08012 0.07818 -0.0126 1.0000 0.0126
-7.500 -0.4992 0.07529 0.07334 -0.0180 1.0000 0.0130
-7.250 -0.4886 0.07032 0.06834 -0.0231 1.0000 0.0135
-7.000 -0.4757 0.06531 0.06327 -0.0278 1.0000 0.0141
-6.750 -0.3827 0.04642 0.04435 -0.0398 0.9709 0.0170
-6.500 -0.3738 0.04153 0.03931 -0.0410 0.9578 0.0170
-6.250 -0.3660 0.03708 0.03469 -0.0410 0.9460 0.0170
-6.000 -0.3569 0.03278 0.03020 -0.0405 0.9357 0.0171
-5.750 -0.3466 0.02868 0.02587 -0.0396 0.9269 0.0171
-5.500 -0.3487 0.02003 0.01686 -0.0390 0.9180 0.0182
-5.250 -0.3335 0.01735 0.01401 -0.0382 0.9102 0.0188
-5.000 -0.3166 0.01512 0.01159 -0.0373 0.9027 0.0197
-4.750 -0.2974 0.01296 0.00920 -0.0364 0.8951 0.0208
-4.500 -0.2775 0.01090 0.00684 -0.0351 0.8884 0.0226
-4.250 -0.2485 0.01127 0.00690 -0.0339 0.8800 0.0266
-4.000 -0.2411 0.01753 0.01196 -0.0316 0.8901 0.0178
-3.750 -0.2171 0.01576 0.01000 -0.0310 0.8828 0.0199
-3.500 -0.1915 0.01433 0.00835 -0.0302 0.8759 0.0205
-3.250 -0.1652 0.01303 0.00687 -0.0294 0.8686 0.0213
-3.000 -0.1396 0.01213 0.00584 -0.0287 0.8613 0.0225
-2.750 -0.1132 0.01150 0.00514 -0.0282 0.8527 0.0244
-2.500 -0.0874 0.01096 0.00448 -0.0276 0.8447 0.0259
-2.250 -0.0613 0.01040 0.00383 -0.0270 0.8351 0.0268
-2.000 -0.0360 0.00961 0.00293 -0.0264 0.8256 0.0296
-1.750 -0.0095 0.00929 0.00254 -0.0260 0.8171 0.0338
-1.500 0.0178 0.00898 0.00216 -0.0257 0.8082 0.0424
-1.250 0.0417 0.00794 0.00188 -0.0254 0.7998 0.2604
-1.000 0.0588 0.00633 0.00170 -0.0238 0.7916 0.6840
-0.750 0.0798 0.00574 0.00187 -0.0212 0.7826 0.9376
-0.500 0.1526 0.00602 0.00202 -0.0303 0.7754 0.9932
-0.250 0.1986 0.00605 0.00194 -0.0344 0.7654 1.0000
0.000 0.2256 0.00604 0.00184 -0.0343 0.7539 1.0000
0.250 0.2526 0.00604 0.00176 -0.0342 0.7416 1.0000
0.500 0.2795 0.00605 0.00168 -0.0341 0.7289 1.0000
0.750 0.3063 0.00607 0.00162 -0.0339 0.7159 1.0000
1.000 0.3329 0.00609 0.00157 -0.0338 0.7020 1.0000
1.250 0.3595 0.00613 0.00153 -0.0336 0.6859 1.0000
1.500 0.3859 0.00619 0.00151 -0.0333 0.6689 1.0000
1.750 0.4124 0.00626 0.00150 -0.0332 0.6535 1.0000
2.000 0.4390 0.00633 0.00152 -0.0330 0.6393 1.0000
2.250 0.4654 0.00641 0.00155 -0.0328 0.6248 1.0000
2.500 0.4918 0.00649 0.00161 -0.0326 0.6100 1.0000
2.750 0.5180 0.00659 0.00166 -0.0324 0.5949 1.0000
3.000 0.5442 0.00670 0.00174 -0.0321 0.5791 1.0000
3.250 0.5702 0.00683 0.00182 -0.0319 0.5620 1.0000
3.500 0.5961 0.00697 0.00194 -0.0316 0.5439 1.0000
3.750 0.6219 0.00712 0.00205 -0.0313 0.5218 1.0000
4.000 0.6475 0.00730 0.00218 -0.0310 0.4975 1.0000
4.250 0.6729 0.00751 0.00233 -0.0307 0.4744 1.0000
4.500 0.6981 0.00775 0.00250 -0.0304 0.4473 1.0000
4.750 0.7222 0.00815 0.00274 -0.0299 0.3963 1.0000
5.000 0.7455 0.00866 0.00301 -0.0294 0.3396 1.0000
5.250 0.7674 0.00940 0.00338 -0.0288 0.2580 1.0000
5.500 0.7865 0.01059 0.00399 -0.0280 0.1476 1.0000
5.750 0.8071 0.01154 0.00462 -0.0273 0.0771 1.0000
6.000 0.8263 0.01279 0.00558 -0.0261 0.0200 1.0000
6.250 0.8483 0.01359 0.00648 -0.0252 0.0153 1.0000
6.500 0.8708 0.01426 0.00725 -0.0244 0.0139 1.0000
6.750 0.8924 0.01506 0.00815 -0.0235 0.0127 1.0000
7.000 0.9126 0.01601 0.00919 -0.0224 0.0117 1.0000
7.250 0.9312 0.01720 0.01047 -0.0211 0.0111 1.0000
7.500 0.9487 0.01859 0.01197 -0.0196 0.0107 1.0000
7.750 0.9665 0.02010 0.01361 -0.0182 0.0106 1.0000
8.000 0.9828 0.02243 0.01607 -0.0166 0.0101 1.0000
8.250 1.0008 0.02490 0.01875 -0.0153 0.0095 1.0000
8.500 1.0204 0.02672 0.02078 -0.0142 0.0094 1.0000
8.750 1.0382 0.02897 0.02327 -0.0129 0.0093 1.0000
9.000 1.0519 0.03225 0.02687 -0.0112 0.0093 1.0000
13.250 0.6980 0.12360 0.12155 -0.0146 0.0183 1.0000
13.500 0.6843 0.12901 0.12696 -0.0167 0.0182 1.0000
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Polar data table (+)
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