EPPLER 502 AIRFOIL (e502-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 502 AIRFOIL (e502-il) Reynolds number: 100,000 Max Cl/Cd: 36.16 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e502-il-100000-n5.txt Download as CSV file: xf-e502-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 502 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4999 0.08643 0.08164 -0.0605 1.0000 0.0173
-12.000 -0.5148 0.08021 0.07540 -0.0643 1.0000 0.0171
-11.750 -0.5387 0.07372 0.06881 -0.0676 1.0000 0.0171
-11.500 -0.5573 0.06904 0.06404 -0.0690 1.0000 0.0169
-11.250 -0.5789 0.06463 0.05952 -0.0693 1.0000 0.0169
-11.000 -0.5966 0.06120 0.05598 -0.0686 1.0000 0.0168
-10.750 -0.6114 0.05729 0.05187 -0.0685 0.9759 0.0168
-10.500 -0.6188 0.05268 0.04685 -0.0699 0.9425 0.0168
-10.250 -0.6214 0.04868 0.04240 -0.0700 0.9233 0.0169
-10.000 -0.6242 0.04510 0.03829 -0.0684 0.9078 0.0172
-9.750 -0.6216 0.04242 0.03518 -0.0664 0.8956 0.0173
-9.500 -0.6174 0.03964 0.03201 -0.0641 0.8856 0.0176
-9.250 -0.6074 0.03753 0.02965 -0.0625 0.8771 0.0183
-9.000 -0.5936 0.03572 0.02759 -0.0612 0.8701 0.0192
-8.750 -0.5768 0.03412 0.02569 -0.0601 0.8636 0.0204
-8.500 -0.5575 0.03268 0.02392 -0.0592 0.8580 0.0231
-8.250 -0.5299 0.03054 0.02149 -0.0595 0.8539 0.0254
-8.000 -0.5054 0.02909 0.01997 -0.0595 0.8487 0.0279
-7.750 -0.4814 0.02811 0.01873 -0.0591 0.8438 0.0328
-7.500 -0.4551 0.02660 0.01720 -0.0594 0.8402 0.0372
-7.250 -0.4334 0.02582 0.01628 -0.0587 0.8352 0.0436
-7.000 -0.4145 0.02478 0.01523 -0.0577 0.8310 0.0496
-6.750 -0.3946 0.02412 0.01440 -0.0566 0.8274 0.0566
-6.500 -0.3797 0.02329 0.01360 -0.0549 0.8230 0.0634
-6.250 -0.3639 0.02266 0.01294 -0.0533 0.8185 0.0730
-6.000 -0.3481 0.02204 0.01228 -0.0515 0.8147 0.0850
-5.750 -0.3324 0.02138 0.01171 -0.0497 0.8114 0.1058
-5.500 -0.3192 0.02066 0.01130 -0.0478 0.8074 0.1548
-5.250 -0.3124 0.01975 0.01088 -0.0448 0.8033 0.2515
-5.000 -0.3161 0.01869 0.01047 -0.0398 0.7995 0.3771
-4.750 -0.2723 0.01994 0.01300 -0.0387 0.7980 0.6514
-4.500 -0.2767 0.01989 0.01284 -0.0334 0.7931 0.6846
-4.250 -0.2680 0.02030 0.01310 -0.0296 0.7894 0.7127
-4.000 -0.2440 0.02123 0.01388 -0.0275 0.7867 0.7377
-3.750 -0.1972 0.02284 0.01530 -0.0282 0.7849 0.7603
-3.500 -0.1588 0.02368 0.01595 -0.0288 0.7828 0.7742
-3.250 -0.1339 0.02407 0.01624 -0.0279 0.7792 0.7855
-3.000 -0.1004 0.02444 0.01644 -0.0285 0.7766 0.7937
-2.750 -0.0745 0.02451 0.01639 -0.0283 0.7738 0.8002
-2.500 -0.0453 0.02448 0.01622 -0.0287 0.7714 0.8038
-2.250 -0.0416 0.02421 0.01586 -0.0250 0.7682 0.8118
-2.000 -0.0131 0.02428 0.01584 -0.0255 0.7648 0.8140
-1.750 0.0128 0.02428 0.01577 -0.0256 0.7617 0.8167
-1.250 0.0399 0.02392 0.01523 -0.0215 0.7559 0.8265
-1.000 0.0666 0.02396 0.01522 -0.0217 0.7530 0.8284
-0.750 0.0877 0.02406 0.01530 -0.0211 0.7492 0.8309
-0.500 0.1069 0.02403 0.01523 -0.0201 0.7458 0.8341
-0.250 0.1181 0.02385 0.01499 -0.0176 0.7429 0.8386
0.000 0.1390 0.02372 0.01481 -0.0167 0.7408 0.8414
0.250 0.1559 0.02397 0.01508 -0.0155 0.7358 0.8437
0.500 0.1756 0.02402 0.01513 -0.0146 0.7320 0.8461
0.750 0.1964 0.02398 0.01506 -0.0138 0.7291 0.8489
1.000 0.2158 0.02383 0.01488 -0.0126 0.7268 0.8518
1.250 0.2188 0.02407 0.01516 -0.0091 0.7207 0.8557
1.500 0.2416 0.02415 0.01526 -0.0087 0.7169 0.8577
1.750 0.2674 0.02411 0.01521 -0.0086 0.7141 0.8594
2.000 0.2948 0.02399 0.01509 -0.0088 0.7120 0.8611
2.250 0.2937 0.02440 0.01556 -0.0047 0.7040 0.8656
2.500 0.3122 0.02428 0.01545 -0.0034 0.7005 0.8689
2.750 0.3436 0.02415 0.01535 -0.0041 0.6982 0.8700
3.000 0.3501 0.02463 0.01592 -0.0013 0.6902 0.8728
3.250 0.3762 0.02457 0.01590 -0.0013 0.6865 0.8746
3.500 0.4078 0.02435 0.01572 -0.0020 0.6840 0.8764
3.750 0.4071 0.02480 0.01626 0.0021 0.6749 0.8814
4.000 0.4358 0.02457 0.01608 0.0019 0.6713 0.8836
4.500 0.4769 0.02471 0.01641 0.0036 0.6586 0.8881
4.750 0.5133 0.02429 0.01608 0.0024 0.6556 0.8896
5.000 0.5168 0.02468 0.01657 0.0058 0.6454 0.8943
5.250 0.5527 0.02413 0.01611 0.0047 0.6417 0.8965
5.500 0.5616 0.02444 0.01655 0.0073 0.6312 0.9006
5.750 0.6023 0.02374 0.01599 0.0057 0.6271 0.9020
6.000 0.6085 0.02399 0.01638 0.0088 0.6158 0.9072
6.250 0.6202 0.02401 0.01652 0.0112 0.6054 0.9122
6.750 0.6729 0.02317 0.01600 0.0121 0.5858 0.9187
7.000 0.6824 0.02317 0.01613 0.0149 0.5721 0.9256
7.250 0.7046 0.02303 0.01615 0.0157 0.5570 0.9305
7.500 0.7137 0.02353 0.01680 0.0176 0.5368 0.9391
7.750 0.7443 0.02314 0.01654 0.0172 0.5151 0.9436
8.000 0.7718 0.02293 0.01642 0.0171 0.4841 0.9494
8.250 0.8024 0.02250 0.01589 0.0171 0.4399 0.9549
8.500 0.8260 0.02284 0.01597 0.0172 0.3837 0.9615
8.750 0.8404 0.02393 0.01680 0.0175 0.3310 0.9724
9.000 0.8528 0.02531 0.01798 0.0174 0.2827 0.9880
9.250 0.8537 0.02657 0.01905 0.0194 0.2473 1.0000
9.500 0.8503 0.02775 0.02005 0.0224 0.2180 1.0000
9.750 0.8505 0.02912 0.02123 0.0247 0.1877 1.0000
10.250 0.8573 0.03198 0.02384 0.0281 0.1348 1.0000
10.500 0.8622 0.03346 0.02523 0.0295 0.1129 1.0000
10.750 0.8663 0.03507 0.02672 0.0309 0.0942 1.0000
11.000 0.8709 0.03672 0.02829 0.0321 0.0785 1.0000
11.250 0.8753 0.03844 0.02995 0.0333 0.0667 1.0000
11.500 0.8797 0.04021 0.03172 0.0344 0.0567 1.0000
11.750 0.8849 0.04198 0.03354 0.0354 0.0481 1.0000
12.000 0.8870 0.04404 0.03558 0.0364 0.0429 1.0000
12.250 0.8924 0.04590 0.03756 0.0373 0.0374 1.0000
12.500 0.8923 0.04829 0.03991 0.0381 0.0336 1.0000
12.750 0.8988 0.05020 0.04206 0.0389 0.0301 1.0000
13.000 0.9031 0.05233 0.04427 0.0394 0.0273 1.0000
13.250 0.9037 0.05486 0.04683 0.0398 0.0250 1.0000
13.500 0.9089 0.05712 0.04926 0.0403 0.0228 1.0000
13.750 0.9133 0.05955 0.05184 0.0408 0.0210 1.0000
14.000 0.9154 0.06220 0.05461 0.0410 0.0194 1.0000
14.250 0.9163 0.06501 0.05749 0.0409 0.0184 1.0000
14.500 0.9198 0.06773 0.06032 0.0410 0.0180 1.0000
14.750 0.9187 0.07108 0.06387 0.0408 0.0168 1.0000
15.000 0.9166 0.07468 0.06773 0.0402 0.0158 1.0000
15.250 0.9125 0.07858 0.07186 0.0394 0.0150 1.0000
15.500 0.9073 0.08278 0.07627 0.0383 0.0145 1.0000
15.750 0.9000 0.08745 0.08114 0.0369 0.0142 1.0000
16.000 0.8915 0.09249 0.08639 0.0350 0.0142 1.0000
16.250 0.8797 0.09827 0.09237 0.0325 0.0139 1.0000
16.500 0.8662 0.10463 0.09893 0.0295 0.0137 1.0000
16.750 0.8503 0.11184 0.10636 0.0258 0.0139 1.0000
17.000 0.8309 0.12028 0.11500 0.0211 0.0138 1.0000
17.250 0.8084 0.13012 0.12504 0.0154 0.0141 1.0000
17.500 0.7780 0.14304 0.13812 0.0080 0.0149 1.0000
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