ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 20% AIRFOIL (arad20-il) Reynolds number: 100,000 Max Cl/Cd: 24.85 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad20-il-100000.txt Download as CSV file: xf-arad20-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 20% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6204 0.08316 0.07801 -0.0337 1.0000 0.0844
-11.500 -0.6560 0.07447 0.06920 -0.0387 1.0000 0.0833
-11.250 -0.7071 0.06663 0.06111 -0.0412 1.0000 0.0819
-11.000 -0.7558 0.06062 0.05473 -0.0393 1.0000 0.0808
-10.750 -0.7785 0.05552 0.04923 -0.0376 1.0000 0.0807
-10.500 -0.7836 0.05161 0.04496 -0.0362 1.0000 0.0816
-10.250 -0.7843 0.04786 0.04075 -0.0348 1.0000 0.0832
-10.000 -0.7826 0.04413 0.03635 -0.0333 1.0000 0.0851
-9.750 -0.7556 0.04284 0.03537 -0.0334 1.0000 0.0876
-9.500 -0.7378 0.04062 0.03295 -0.0328 1.0000 0.0902
-9.250 -0.7224 0.03800 0.02981 -0.0321 1.0000 0.0932
-9.000 -0.6959 0.03677 0.02890 -0.0324 1.0000 0.0965
-8.750 -0.6751 0.03509 0.02703 -0.0324 1.0000 0.1005
-8.500 -0.6192 0.03323 0.02513 -0.0384 0.9115 0.1067
-8.250 -0.5943 0.03203 0.02342 -0.0373 0.8423 0.1119
-8.000 -0.5723 0.03134 0.02260 -0.0357 0.7984 0.1167
-7.750 -0.5486 0.03035 0.02128 -0.0346 0.7693 0.1226
-7.500 -0.5231 0.02962 0.02046 -0.0340 0.7467 0.1289
-7.250 -0.4971 0.02872 0.01945 -0.0334 0.7279 0.1360
-7.000 -0.4700 0.02806 0.01854 -0.0331 0.7114 0.1448
-6.750 -0.4434 0.02730 0.01787 -0.0328 0.6981 0.1538
-6.500 -0.4159 0.02654 0.01713 -0.0326 0.6851 0.1645
-6.250 -0.3887 0.02590 0.01646 -0.0324 0.6742 0.1775
-6.000 -0.3609 0.02526 0.01587 -0.0324 0.6629 0.1932
-5.750 -0.3340 0.02475 0.01535 -0.0320 0.6540 0.2119
-5.500 -0.3053 0.02419 0.01490 -0.0323 0.6439 0.2360
-5.250 -0.2782 0.02365 0.01451 -0.0321 0.6352 0.2634
-5.000 -0.2503 0.02325 0.01424 -0.0321 0.6271 0.2983
-4.750 -0.2221 0.02285 0.01408 -0.0323 0.6182 0.3390
-4.500 -0.1947 0.02259 0.01398 -0.0320 0.6108 0.3834
-4.250 -0.1667 0.02247 0.01406 -0.0319 0.6033 0.4298
-4.000 -0.1383 0.02238 0.01418 -0.0318 0.5950 0.4755
-3.750 -0.1107 0.02242 0.01431 -0.0313 0.5880 0.5185
-3.500 -0.0829 0.02261 0.01457 -0.0308 0.5815 0.5587
-3.250 -0.0546 0.02275 0.01485 -0.0304 0.5735 0.5964
-3.000 -0.0278 0.02293 0.01510 -0.0294 0.5665 0.6294
-2.750 -0.0016 0.02329 0.01540 -0.0283 0.5608 0.6612
-2.500 0.0260 0.02355 0.01577 -0.0277 0.5533 0.6922
-2.250 0.0513 0.02380 0.01610 -0.0263 0.5463 0.7190
-2.000 0.0757 0.02409 0.01634 -0.0246 0.5405 0.7449
-1.750 0.0997 0.02449 0.01675 -0.0230 0.5346 0.7698
-1.500 0.1234 0.02478 0.01712 -0.0214 0.5273 0.7940
-1.250 0.1459 0.02499 0.01730 -0.0193 0.5211 0.8176
-1.000 0.1676 0.02523 0.01743 -0.0170 0.5161 0.8408
-0.750 0.1895 0.02557 0.01783 -0.0152 0.5098 0.8638
-0.500 0.2122 0.02577 0.01804 -0.0134 0.5028 0.8871
-0.250 0.2371 0.02585 0.01803 -0.0120 0.4971 0.9109
0.000 0.2685 0.02609 0.01809 -0.0118 0.4922 0.9323
0.250 0.3097 0.02661 0.01873 -0.0146 0.4836 0.9503
0.500 0.3596 0.02693 0.01893 -0.0188 0.4762 0.9651
0.750 0.4168 0.02733 0.01907 -0.0242 0.4704 0.9752
1.000 0.4721 0.02815 0.02002 -0.0305 0.4609 0.9851
1.250 0.5267 0.02839 0.02013 -0.0360 0.4539 0.9954
1.500 0.5586 0.02845 0.01999 -0.0375 0.4495 1.0000
1.750 0.5681 0.02901 0.02065 -0.0361 0.4438 1.0000
2.000 0.5779 0.02940 0.02106 -0.0343 0.4380 1.0000
2.250 0.5915 0.02950 0.02106 -0.0325 0.4335 1.0000
2.500 0.6120 0.02957 0.02096 -0.0315 0.4298 1.0000
2.750 0.6342 0.03047 0.02188 -0.0316 0.4242 1.0000
3.000 0.6579 0.03143 0.02291 -0.0320 0.4173 1.0000
3.250 0.6865 0.03166 0.02302 -0.0324 0.4127 1.0000
3.500 0.7170 0.03174 0.02290 -0.0327 0.4091 1.0000
3.750 0.7385 0.03328 0.02461 -0.0332 0.4022 1.0000
4.000 0.7634 0.03421 0.02557 -0.0336 0.3963 1.0000
4.250 0.7933 0.03432 0.02556 -0.0339 0.3923 1.0000
4.500 0.8252 0.03429 0.02533 -0.0342 0.3892 1.0000
4.750 0.8387 0.03673 0.02807 -0.0343 0.3814 1.0000
5.000 0.8631 0.03758 0.02892 -0.0344 0.3764 1.0000
5.250 0.8941 0.03753 0.02876 -0.0347 0.3730 1.0000
5.500 0.9275 0.03733 0.02836 -0.0350 0.3703 1.0000
5.750 0.9256 0.04129 0.03276 -0.0343 0.3618 1.0000
6.000 0.9492 0.04207 0.03353 -0.0343 0.3575 1.0000
6.250 0.9825 0.04174 0.03308 -0.0345 0.3546 1.0000
6.500 1.0188 0.04123 0.03237 -0.0350 0.3522 1.0000
6.750 0.9576 0.05084 0.04271 -0.0318 0.3413 1.0000
7.000 0.9937 0.05010 0.04187 -0.0319 0.3386 1.0000
7.250 1.0403 0.04842 0.04003 -0.0325 0.3367 1.0000
7.500 1.0853 0.04706 0.03847 -0.0333 0.3348 1.0000
7.750 0.6404 0.10814 0.10069 -0.0435 0.3143 1.0000
8.000 0.6357 0.11368 0.10626 -0.0451 0.3149 1.0000
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Polar data table (+)
Polar graphs
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