WORTMANN FX 77-080 (fx77080-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 77-080 (fx77080-il) Reynolds number: 200,000 Max Cl/Cd: 41.98 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77080-il-200000.txt Download as CSV file: xf-fx77080-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5721 0.07729 0.07387 -0.0107 1.0000 0.0620
-9.750 -0.8243 0.05667 0.05258 -0.0267 1.0000 0.0359
-9.500 -0.8410 0.05144 0.04712 -0.0255 1.0000 0.0353
-9.250 -0.8519 0.04649 0.04185 -0.0237 1.0000 0.0347
-9.000 -0.8576 0.04172 0.03666 -0.0216 1.0000 0.0342
-8.750 -0.8572 0.03746 0.03191 -0.0192 1.0000 0.0342
-8.500 -0.8509 0.03382 0.02780 -0.0169 1.0000 0.0341
-8.250 -0.8399 0.03086 0.02439 -0.0148 1.0000 0.0347
-8.000 -0.8245 0.02883 0.02194 -0.0128 1.0000 0.0361
-7.750 -0.8096 0.02625 0.01897 -0.0110 1.0000 0.0377
-7.500 -0.7912 0.02422 0.01685 -0.0097 1.0000 0.0398
-7.250 -0.7710 0.02281 0.01529 -0.0084 1.0000 0.0420
-7.000 -0.7499 0.02151 0.01380 -0.0070 1.0000 0.0444
-6.750 -0.7282 0.02058 0.01266 -0.0057 1.0000 0.0475
-6.500 -0.7086 0.01883 0.01093 -0.0043 1.0000 0.0516
-6.250 -0.6872 0.01791 0.00993 -0.0030 1.0000 0.0562
-6.000 -0.6669 0.01678 0.00876 -0.0015 1.0000 0.0617
-5.750 -0.6454 0.01610 0.00805 -0.0002 1.0000 0.0695
-5.500 -0.6253 0.01521 0.00720 0.0013 1.0000 0.0797
-5.250 -0.6041 0.01457 0.00659 0.0027 1.0000 0.0957
-5.000 -0.5835 0.01391 0.00605 0.0041 1.0000 0.1182
-4.750 -0.5620 0.01343 0.00563 0.0053 1.0000 0.1434
-4.500 -0.5403 0.01302 0.00525 0.0065 1.0000 0.1652
-4.250 -0.5185 0.01262 0.00489 0.0077 1.0000 0.1851
-4.000 -0.4972 0.01221 0.00457 0.0090 1.0000 0.2057
-3.750 -0.4757 0.01183 0.00427 0.0102 1.0000 0.2292
-3.500 -0.4549 0.01140 0.00398 0.0115 1.0000 0.2594
-3.250 -0.4349 0.01093 0.00373 0.0130 1.0000 0.3017
-3.000 -0.4165 0.01038 0.00351 0.0148 1.0000 0.3658
-2.750 -0.3994 0.00982 0.00335 0.0169 1.0000 0.4521
-2.500 -0.3837 0.00928 0.00327 0.0194 1.0000 0.5503
-2.250 -0.3681 0.00883 0.00325 0.0222 1.0000 0.6493
-2.000 -0.3500 0.00850 0.00331 0.0248 1.0000 0.7422
-1.750 -0.3244 0.00834 0.00342 0.0260 1.0000 0.8275
-1.500 -0.2801 0.00838 0.00356 0.0234 1.0000 0.9000
-1.250 -0.2206 0.00853 0.00368 0.0174 1.0000 0.9411
-1.000 -0.1609 0.00869 0.00377 0.0112 1.0000 0.9640
-0.750 -0.1051 0.00881 0.00384 0.0056 1.0000 0.9804
-0.500 -0.0477 0.00886 0.00384 -0.0004 1.0000 0.9925
-0.250 -0.0050 0.00886 0.00382 -0.0038 1.0000 1.0000
0.000 0.0000 0.00883 0.00379 0.0000 1.0000 1.0000
0.250 0.0051 0.00886 0.00382 0.0038 1.0000 1.0000
0.500 0.0474 0.00886 0.00384 0.0005 0.9926 1.0000
0.750 0.1056 0.00881 0.00383 -0.0057 0.9801 1.0000
1.000 0.1623 0.00868 0.00376 -0.0114 0.9634 1.0000
1.250 0.2216 0.00853 0.00368 -0.0175 0.9400 1.0000
1.500 0.2801 0.00838 0.00356 -0.0233 0.9005 1.0000
1.750 0.3244 0.00834 0.00342 -0.0260 0.8277 1.0000
2.000 0.3500 0.00851 0.00331 -0.0247 0.7406 1.0000
2.250 0.3680 0.00884 0.00325 -0.0221 0.6482 1.0000
2.500 0.3837 0.00928 0.00326 -0.0194 0.5489 1.0000
2.750 0.3995 0.00981 0.00335 -0.0168 0.4525 1.0000
3.000 0.4164 0.01039 0.00351 -0.0147 0.3644 1.0000
3.250 0.4349 0.01093 0.00373 -0.0130 0.3008 1.0000
3.500 0.4549 0.01141 0.00398 -0.0115 0.2588 1.0000
3.750 0.4756 0.01183 0.00427 -0.0102 0.2292 1.0000
4.000 0.4971 0.01221 0.00458 -0.0089 0.2059 1.0000
4.250 0.5185 0.01263 0.00489 -0.0077 0.1853 1.0000
4.500 0.5402 0.01302 0.00525 -0.0065 0.1653 1.0000
4.750 0.5619 0.01343 0.00563 -0.0053 0.1434 1.0000
5.000 0.5835 0.01390 0.00605 -0.0041 0.1185 1.0000
5.250 0.6040 0.01458 0.00660 -0.0027 0.0960 1.0000
5.500 0.6252 0.01523 0.00722 -0.0013 0.0798 1.0000
6.000 0.6669 0.01678 0.00876 0.0015 0.0618 1.0000
6.250 0.6872 0.01789 0.00992 0.0030 0.0560 1.0000
6.500 0.7086 0.01881 0.01090 0.0043 0.0514 1.0000
6.750 0.7279 0.02063 0.01271 0.0057 0.0471 1.0000
7.000 0.7499 0.02144 0.01375 0.0070 0.0441 1.0000
7.250 0.7709 0.02280 0.01528 0.0084 0.0418 1.0000
7.500 0.7912 0.02423 0.01686 0.0097 0.0398 1.0000
7.750 0.8095 0.02630 0.01903 0.0110 0.0378 1.0000
8.000 0.8242 0.02893 0.02208 0.0129 0.0360 1.0000
8.250 0.8396 0.03099 0.02453 0.0148 0.0350 1.0000
8.500 0.8508 0.03388 0.02787 0.0169 0.0342 1.0000
8.750 0.8569 0.03753 0.03198 0.0192 0.0341 1.0000
9.000 0.8573 0.04181 0.03673 0.0216 0.0343 1.0000
9.250 0.8511 0.04668 0.04202 0.0238 0.0348 1.0000
9.500 0.8397 0.05168 0.04735 0.0255 0.0353 1.0000
9.750 0.8262 0.05665 0.05250 0.0266 0.0361 1.0000
10.000 0.8262 0.06030 0.05626 0.0276 0.0375 1.0000
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Polar data table (+)
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