WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Reynolds number: 500,000 Max Cl/Cd: 106.84 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx08s176-il-500000-n5.txt Download as CSV file: xf-fx08s176-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 08-S-176 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1096 0.09676 0.09234 -0.0873 0.5725 0.0080
-11.250 -0.1128 0.09192 0.08753 -0.0893 0.5721 0.0081
-11.000 -0.1225 0.08591 0.08156 -0.0918 0.5716 0.0082
-10.750 -0.1239 0.08206 0.07774 -0.0938 0.5708 0.0085
-10.500 -0.1287 0.07752 0.07323 -0.0961 0.5702 0.0086
-10.250 -0.1306 0.07365 0.06940 -0.0983 0.5695 0.0087
-10.000 -0.1544 0.06566 0.06149 -0.1035 0.5691 0.0087
-9.750 -0.2233 0.05308 0.04889 -0.1102 0.5690 0.0086
-9.500 -0.3010 0.04340 0.03896 -0.1047 0.5688 0.0087
-9.250 -0.3714 0.02984 0.02454 -0.0969 0.5687 0.0092
-9.000 -0.3588 0.02827 0.02277 -0.0954 0.5678 0.0096
-8.750 -0.3491 0.02597 0.02013 -0.0935 0.5670 0.0101
-8.500 -0.3353 0.02400 0.01781 -0.0920 0.5662 0.0108
-8.250 -0.3177 0.02248 0.01599 -0.0908 0.5654 0.0114
-8.000 -0.2964 0.02160 0.01490 -0.0901 0.5646 0.0119
-7.750 -0.2753 0.02081 0.01400 -0.0894 0.5638 0.0124
-7.500 -0.2518 0.02041 0.01353 -0.0890 0.5630 0.0128
-7.250 -0.2279 0.02002 0.01305 -0.0887 0.5622 0.0133
-7.000 -0.2043 0.01940 0.01229 -0.0883 0.5612 0.0138
-6.750 -0.1800 0.01880 0.01157 -0.0879 0.5603 0.0145
-6.500 -0.1552 0.01828 0.01093 -0.0876 0.5595 0.0153
-6.250 -0.1299 0.01783 0.01037 -0.0873 0.5586 0.0160
-6.000 -0.1041 0.01748 0.00992 -0.0871 0.5578 0.0164
-5.750 -0.0807 0.01647 0.00881 -0.0866 0.5569 0.0172
-5.500 -0.0556 0.01599 0.00829 -0.0864 0.5561 0.0179
-5.250 -0.0300 0.01566 0.00794 -0.0862 0.5552 0.0187
-5.000 -0.0042 0.01535 0.00759 -0.0860 0.5543 0.0195
-4.750 0.0214 0.01499 0.00717 -0.0858 0.5534 0.0203
-4.500 0.0468 0.01462 0.00675 -0.0856 0.5525 0.0208
-4.250 0.0725 0.01430 0.00636 -0.0853 0.5516 0.0214
-4.000 0.0982 0.01400 0.00601 -0.0851 0.5506 0.0219
-3.750 0.1242 0.01374 0.00570 -0.0850 0.5497 0.0225
-3.500 0.1492 0.01336 0.00528 -0.0847 0.5489 0.0239
-3.250 0.1755 0.01313 0.00503 -0.0846 0.5481 0.0251
-3.000 0.2021 0.01296 0.00482 -0.0846 0.5473 0.0261
-2.750 0.2291 0.01284 0.00464 -0.0847 0.5465 0.0274
-2.500 0.2561 0.01271 0.00449 -0.0847 0.5457 0.0288
-2.250 0.2832 0.01258 0.00436 -0.0848 0.5449 0.0309
-2.000 0.3102 0.01244 0.00426 -0.0849 0.5440 0.0369
-1.750 0.3372 0.01229 0.00420 -0.0850 0.5428 0.0556
-1.500 0.3646 0.01219 0.00414 -0.0852 0.5417 0.0697
-1.250 0.3922 0.01212 0.00408 -0.0854 0.5407 0.0809
-1.000 0.4193 0.01195 0.00402 -0.0856 0.5398 0.1151
-0.750 0.4453 0.01156 0.00397 -0.0858 0.5388 0.2263
-0.500 0.4675 0.01006 0.00382 -0.0863 0.5378 0.6483
-0.250 0.4884 0.00991 0.00419 -0.0845 0.5367 0.7880
0.000 0.5146 0.01010 0.00437 -0.0841 0.5354 0.8212
0.250 0.5414 0.01028 0.00451 -0.0838 0.5342 0.8377
0.500 0.5695 0.01042 0.00458 -0.0839 0.5329 0.8475
0.750 0.5958 0.01053 0.00467 -0.0837 0.5315 0.8517
1.000 0.6233 0.01059 0.00474 -0.0838 0.5297 0.8553
1.250 0.6519 0.01065 0.00477 -0.0842 0.5278 0.8602
1.500 0.6786 0.01070 0.00482 -0.0841 0.5258 0.8633
1.750 0.7046 0.01075 0.00487 -0.0839 0.5239 0.8665
2.000 0.7312 0.01083 0.00493 -0.0838 0.5223 0.8710
2.250 0.7600 0.01088 0.00495 -0.0843 0.5211 0.8741
2.500 0.7895 0.01093 0.00497 -0.0850 0.5199 0.8762
2.750 0.8167 0.01098 0.00500 -0.0851 0.5188 0.8775
3.000 0.8438 0.01105 0.00507 -0.0853 0.5176 0.8789
3.250 0.8708 0.01111 0.00517 -0.0855 0.5160 0.8804
3.500 0.8980 0.01118 0.00527 -0.0857 0.5143 0.8819
3.750 0.9255 0.01124 0.00535 -0.0860 0.5124 0.8835
4.000 0.9532 0.01129 0.00542 -0.0864 0.5105 0.8853
4.250 0.9812 0.01133 0.00548 -0.0868 0.5086 0.8870
4.500 1.0096 0.01137 0.00552 -0.0873 0.5070 0.8884
4.750 1.0383 0.01143 0.00557 -0.0880 0.5054 0.8898
5.000 1.0660 0.01150 0.00567 -0.0884 0.5037 0.8911
5.250 1.0918 0.01158 0.00582 -0.0884 0.5016 0.8924
5.500 1.1178 0.01165 0.00596 -0.0885 0.4993 0.8936
5.750 1.1440 0.01172 0.00609 -0.0886 0.4969 0.8950
6.000 1.1704 0.01178 0.00618 -0.0887 0.4946 0.8963
6.250 1.1966 0.01180 0.00620 -0.0888 0.4914 0.8977
6.500 1.2219 0.01185 0.00632 -0.0888 0.4847 0.8992
6.750 1.2467 0.01186 0.00632 -0.0887 0.4764 0.9005
7.000 1.2709 0.01194 0.00643 -0.0886 0.4656 0.9016
7.250 1.2927 0.01210 0.00655 -0.0880 0.4505 0.9028
7.500 1.3085 0.01247 0.00681 -0.0865 0.4246 0.9042
7.750 1.3129 0.01319 0.00737 -0.0830 0.3941 0.9061
8.000 1.3107 0.01394 0.00803 -0.0783 0.3704 0.9083
8.250 1.3045 0.01492 0.00895 -0.0733 0.3512 0.9109
8.500 1.2980 0.01608 0.01008 -0.0688 0.3348 0.9136
8.750 1.2893 0.01761 0.01159 -0.0649 0.3215 0.9169
9.000 1.2667 0.02048 0.01445 -0.0608 0.3016 0.9202
9.250 1.2545 0.02321 0.01720 -0.0583 0.2879 0.9229
9.500 1.2288 0.02707 0.02101 -0.0552 0.2637 0.9262
9.750 1.2020 0.03100 0.02484 -0.0520 0.2368 0.9298
10.250 1.1506 0.03874 0.03236 -0.0463 0.1818 0.9352
10.500 1.1233 0.04306 0.03648 -0.0437 0.1415 0.9379
10.750 1.0986 0.04752 0.04071 -0.0418 0.0951 0.9405
11.000 1.0781 0.05190 0.04487 -0.0403 0.0479 0.9428
11.250 1.0665 0.05569 0.04852 -0.0395 0.0131 0.9451
11.750 1.0803 0.05977 0.05270 -0.0392 0.0081 0.9502
12.000 1.0885 0.06177 0.05477 -0.0392 0.0074 0.9537
12.250 1.0969 0.06382 0.05689 -0.0394 0.0070 0.9581
12.500 1.1034 0.06624 0.05941 -0.0397 0.0063 0.9645
12.750 1.1115 0.06857 0.06184 -0.0402 0.0060 0.9752
13.250 1.1247 0.07323 0.06664 -0.0408 0.0057 1.0000
13.500 1.1317 0.07562 0.06909 -0.0411 0.0056 1.0000
13.750 1.1375 0.07817 0.07172 -0.0415 0.0053 1.0000
14.000 1.1425 0.08087 0.07449 -0.0419 0.0051 1.0000
14.250 1.1485 0.08345 0.07713 -0.0424 0.0048 1.0000
14.500 1.1522 0.08639 0.08015 -0.0430 0.0046 1.0000
14.750 1.1559 0.08935 0.08318 -0.0435 0.0044 1.0000
15.000 1.1588 0.09243 0.08634 -0.0442 0.0043 1.0000
15.250 1.1613 0.09560 0.08958 -0.0448 0.0042 1.0000
15.500 1.1623 0.09904 0.09309 -0.0456 0.0041 1.0000
15.750 1.1637 0.10244 0.09656 -0.0464 0.0040 1.0000
16.000 1.1620 0.10633 0.10052 -0.0474 0.0039 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il)