DF102 (df102-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: DF102 (df102-il) Reynolds number: 50,000 Max Cl/Cd: 32.65 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-df102-il-50000.txt Download as CSV file: xf-df102-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: DF102
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3927 0.09841 0.09162 -0.0177 1.0000 0.2819
-8.250 -0.3842 0.09466 0.08790 -0.0174 1.0000 0.2858
-8.000 -0.4840 0.08193 0.07555 -0.0364 1.0000 0.1599
-7.750 -0.4830 0.07640 0.07008 -0.0363 1.0000 0.1488
-7.500 -0.4975 0.07069 0.06439 -0.0379 1.0000 0.1379
-7.250 -0.5242 0.06376 0.05734 -0.0399 1.0000 0.1276
-7.000 -0.5573 0.05568 0.04865 -0.0408 1.0000 0.1171
-6.750 -0.5578 0.05169 0.04441 -0.0392 1.0000 0.1168
-6.500 -0.5567 0.04771 0.04004 -0.0375 1.0000 0.1169
-6.250 -0.5516 0.04399 0.03582 -0.0358 1.0000 0.1174
-6.000 -0.5414 0.04064 0.03219 -0.0341 1.0000 0.1188
-5.750 -0.5272 0.03795 0.02934 -0.0324 1.0000 0.1213
-5.500 -0.5121 0.03564 0.02674 -0.0308 1.0000 0.1263
-5.250 -0.4960 0.03314 0.02374 -0.0292 1.0000 0.1333
-5.000 -0.4774 0.03133 0.02181 -0.0277 1.0000 0.1417
-4.750 -0.4583 0.02961 0.01993 -0.0261 1.0000 0.1538
-4.500 -0.4387 0.02811 0.01820 -0.0246 1.0000 0.1744
-4.250 -0.4201 0.02686 0.01717 -0.0228 1.0000 0.2074
-4.000 -0.4042 0.02590 0.01655 -0.0205 1.0000 0.2711
-3.750 -0.3900 0.02538 0.01622 -0.0180 1.0000 0.3396
-3.500 -0.3755 0.02504 0.01611 -0.0154 1.0000 0.3914
-3.250 -0.3592 0.02462 0.01578 -0.0133 1.0000 0.4358
-3.000 -0.3415 0.02414 0.01537 -0.0114 1.0000 0.4732
-2.750 -0.3232 0.02364 0.01485 -0.0097 1.0000 0.5080
-2.500 -0.3043 0.02317 0.01442 -0.0082 1.0000 0.5430
-2.250 -0.2847 0.02274 0.01404 -0.0068 1.0000 0.5821
-2.000 -0.2656 0.02229 0.01372 -0.0052 1.0000 0.6295
-1.750 -0.2482 0.02175 0.01348 -0.0031 1.0000 0.6942
-1.500 -0.1569 0.02101 0.01336 -0.0135 1.0000 1.0000
-1.250 -0.1436 0.02102 0.01284 -0.0136 1.0000 1.0000
-1.000 -0.1276 0.02130 0.01276 -0.0130 1.0000 1.0000
-0.750 -0.1114 0.02166 0.01283 -0.0123 1.0000 1.0000
-0.500 -0.0949 0.02206 0.01298 -0.0117 1.0000 1.0000
-0.250 -0.0784 0.02252 0.01323 -0.0110 1.0000 1.0000
0.000 -0.0617 0.02301 0.01354 -0.0105 1.0000 1.0000
0.250 -0.0450 0.02356 0.01392 -0.0099 1.0000 1.0000
0.500 -0.0283 0.02414 0.01435 -0.0095 1.0000 1.0000
0.750 -0.0070 0.02487 0.01494 -0.0099 0.9980 1.0000
1.000 0.0419 0.02630 0.01622 -0.0155 0.9844 1.0000
1.250 0.0893 0.02765 0.01746 -0.0206 0.9702 1.0000
1.500 0.1331 0.02884 0.01857 -0.0250 0.9551 1.0000
1.750 0.1739 0.02986 0.01953 -0.0286 0.9375 1.0000
2.000 0.2318 0.03085 0.02051 -0.0344 0.9128 1.0000
2.250 0.2847 0.03139 0.02105 -0.0387 0.8851 1.0000
2.500 0.3356 0.03174 0.02144 -0.0423 0.8599 1.0000
2.750 0.3923 0.03183 0.02160 -0.0463 0.8372 1.0000
3.000 0.4335 0.03183 0.02168 -0.0477 0.8131 1.0000
3.250 0.5073 0.03080 0.02084 -0.0528 0.7904 1.0000
3.500 0.5497 0.03007 0.02023 -0.0531 0.7643 1.0000
3.750 0.5984 0.02877 0.01909 -0.0534 0.7374 1.0000
4.000 0.6471 0.02711 0.01756 -0.0529 0.7072 1.0000
4.250 0.6968 0.02509 0.01558 -0.0518 0.6708 1.0000
4.500 0.7262 0.02409 0.01453 -0.0487 0.6201 1.0000
4.750 0.7530 0.02356 0.01371 -0.0455 0.5598 1.0000
5.000 0.7761 0.02377 0.01350 -0.0428 0.5034 1.0000
5.250 0.7975 0.02443 0.01382 -0.0407 0.4590 1.0000
5.500 0.8188 0.02533 0.01452 -0.0391 0.4245 1.0000
5.750 0.8422 0.02630 0.01527 -0.0379 0.3974 1.0000
6.000 0.8652 0.02737 0.01625 -0.0369 0.3747 1.0000
6.250 0.8906 0.02855 0.01731 -0.0363 0.3569 1.0000
6.500 0.9152 0.02982 0.01850 -0.0356 0.3411 1.0000
6.750 0.9379 0.03115 0.01985 -0.0348 0.3267 1.0000
7.000 0.9584 0.03266 0.02157 -0.0337 0.3149 1.0000
7.250 0.9795 0.03440 0.02347 -0.0329 0.3056 1.0000
7.500 1.0053 0.03601 0.02503 -0.0326 0.2965 1.0000
7.750 1.0183 0.03798 0.02739 -0.0309 0.2881 1.0000
8.250 1.0498 0.04228 0.03218 -0.0283 0.2747 1.0000
8.500 1.0663 0.04460 0.03470 -0.0272 0.2698 1.0000
8.750 1.0817 0.04721 0.03748 -0.0262 0.2653 1.0000
9.000 1.0774 0.05061 0.04136 -0.0236 0.2618 1.0000
9.250 1.0750 0.05399 0.04506 -0.0215 0.2580 1.0000
9.500 1.1016 0.05604 0.04710 -0.0213 0.2522 1.0000
9.750 1.0904 0.06043 0.05184 -0.0190 0.2512 1.0000
10.000 1.0689 0.06553 0.05721 -0.0168 0.2513 1.0000
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Polar data table (+)
Polar graphs
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