PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 100,000 Max Cl/Cd: 45.04 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pmc19sm-il-100000-n5.txt Download as CSV file: xf-pmc19sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: PMC19 Smoothed
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4821 0.09035 0.08614 0.0099 1.0000 0.0419
-8.250 -0.4851 0.08586 0.08169 0.0080 1.0000 0.0423
-8.000 -0.4901 0.08112 0.07699 0.0055 1.0000 0.0427
-7.750 -0.4986 0.07620 0.07208 0.0021 1.0000 0.0428
-7.500 -0.5081 0.07172 0.06760 -0.0002 1.0000 0.0430
-7.250 -0.5135 0.06728 0.06312 -0.0017 1.0000 0.0434
-7.000 -0.5148 0.06277 0.05854 -0.0029 1.0000 0.0439
-6.750 -0.5128 0.05831 0.05396 -0.0039 1.0000 0.0446
-6.500 -0.5079 0.05389 0.04943 -0.0047 1.0000 0.0455
-6.250 -0.4998 0.04963 0.04501 -0.0052 1.0000 0.0467
-6.000 -0.4839 0.04777 0.04261 -0.0056 1.0000 0.0506
-5.750 -0.4694 0.04416 0.03870 -0.0053 1.0000 0.0509
-5.250 -0.4757 0.04690 0.04086 -0.0024 1.0000 0.0341
-5.000 -0.4543 0.04316 0.03684 -0.0023 1.0000 0.0313
-4.750 -0.4311 0.04022 0.03363 -0.0021 1.0000 0.0318
-4.500 -0.4066 0.03770 0.03082 -0.0019 1.0000 0.0338
-4.250 -0.3814 0.03492 0.02775 -0.0015 1.0000 0.0337
-4.000 -0.3555 0.03216 0.02466 -0.0012 1.0000 0.0329
-3.750 -0.3287 0.02963 0.02182 -0.0008 1.0000 0.0325
-3.500 -0.3013 0.02736 0.01926 -0.0004 1.0000 0.0327
-3.250 -0.2629 0.02521 0.01672 -0.0021 0.9295 0.0346
-3.000 -0.2264 0.02400 0.01499 -0.0027 0.8824 0.0377
-2.750 -0.1989 0.02199 0.01269 -0.0021 0.8459 0.0388
-2.500 -0.1736 0.02067 0.01119 -0.0011 0.8146 0.0404
-2.250 -0.1488 0.01989 0.01027 -0.0001 0.7859 0.0445
-2.000 -0.1234 0.01906 0.00925 0.0009 0.7597 0.0482
-1.750 -0.0983 0.01822 0.00823 0.0020 0.7353 0.0502
-1.500 -0.0750 0.01730 0.00725 0.0033 0.7128 0.0528
-1.250 -0.0508 0.01680 0.00668 0.0040 0.6903 0.0597
-1.000 -0.0257 0.01637 0.00603 0.0048 0.6692 0.0648
-0.750 -0.0003 0.01587 0.00539 0.0053 0.6485 0.0710
-0.500 0.0258 0.01558 0.00491 0.0057 0.6291 0.0842
-0.250 0.0523 0.01526 0.00448 0.0061 0.6097 0.1049
0.000 0.0671 0.01308 0.00431 0.0083 0.5936 0.6889
0.250 0.0833 0.01306 0.00456 0.0122 0.5775 0.8077
0.500 0.1028 0.01314 0.00461 0.0150 0.5615 0.8558
0.750 0.1203 0.01316 0.00464 0.0189 0.5463 0.9115
1.000 0.1510 0.01319 0.00454 0.0191 0.5302 0.9420
1.250 0.1843 0.01325 0.00442 0.0179 0.5145 0.9501
1.500 0.2177 0.01333 0.00435 0.0166 0.4995 0.9590
1.750 0.2538 0.01343 0.00431 0.0147 0.4847 0.9665
2.000 0.2896 0.01355 0.00432 0.0128 0.4707 0.9751
2.500 0.3611 0.01384 0.00445 0.0088 0.4446 0.9969
2.750 0.3862 0.01399 0.00454 0.0089 0.4337 1.0000
3.000 0.4097 0.01418 0.00465 0.0093 0.4241 1.0000
3.250 0.4345 0.01439 0.00482 0.0096 0.4148 1.0000
3.500 0.4603 0.01461 0.00503 0.0096 0.4051 1.0000
3.750 0.4865 0.01486 0.00523 0.0096 0.3966 1.0000
4.000 0.5132 0.01513 0.00549 0.0095 0.3879 1.0000
4.250 0.5401 0.01541 0.00582 0.0094 0.3799 1.0000
4.500 0.5669 0.01571 0.00612 0.0094 0.3722 1.0000
4.750 0.5941 0.01603 0.00650 0.0092 0.3642 1.0000
5.000 0.6210 0.01637 0.00685 0.0092 0.3576 1.0000
5.250 0.6482 0.01672 0.00731 0.0090 0.3500 1.0000
5.500 0.6752 0.01708 0.00776 0.0090 0.3436 1.0000
5.750 0.7023 0.01748 0.00831 0.0088 0.3367 1.0000
6.000 0.7290 0.01782 0.00870 0.0088 0.3288 1.0000
6.250 0.7552 0.01797 0.00897 0.0088 0.3119 1.0000
6.500 0.7813 0.01806 0.00924 0.0088 0.2907 1.0000
6.750 0.8073 0.01826 0.00953 0.0088 0.2696 1.0000
7.000 0.8333 0.01850 0.00990 0.0087 0.2387 1.0000
7.250 0.8562 0.01938 0.01044 0.0086 0.1419 1.0000
7.500 0.8700 0.02254 0.01280 0.0084 0.0508 1.0000
7.750 0.8915 0.02398 0.01449 0.0085 0.0437 1.0000
8.000 0.9094 0.02588 0.01656 0.0086 0.0382 1.0000
8.250 0.9293 0.02722 0.01816 0.0087 0.0344 1.0000
8.500 0.9464 0.02885 0.01999 0.0090 0.0321 1.0000
8.750 0.9611 0.03062 0.02190 0.0094 0.0303 1.0000
9.000 0.9733 0.03258 0.02393 0.0101 0.0289 1.0000
9.250 0.9850 0.03476 0.02613 0.0112 0.0277 1.0000
9.500 1.0017 0.03626 0.02783 0.0119 0.0262 1.0000
9.750 1.0169 0.03798 0.02971 0.0126 0.0244 1.0000
10.000 1.0318 0.03999 0.03187 0.0134 0.0233 1.0000
10.250 1.0458 0.04223 0.03427 0.0142 0.0225 1.0000
10.500 1.0581 0.04468 0.03690 0.0149 0.0219 1.0000
10.750 1.0678 0.04735 0.03978 0.0155 0.0213 1.0000
11.000 1.0731 0.05017 0.04281 0.0162 0.0209 1.0000
11.250 1.0745 0.05321 0.04605 0.0165 0.0205 1.0000
11.500 1.0733 0.05658 0.04959 0.0162 0.0201 1.0000
11.750 1.0691 0.06059 0.05381 0.0155 0.0196 1.0000
12.250 1.0480 0.06986 0.06350 0.0116 0.0191 1.0000
12.500 1.0353 0.07482 0.06870 0.0084 0.0190 1.0000
12.750 1.0215 0.08033 0.07442 0.0048 0.0190 1.0000
13.000 1.0072 0.08628 0.08056 0.0009 0.0190 1.0000
13.250 0.9920 0.09268 0.08714 -0.0032 0.0190 1.0000
13.500 0.9761 0.09949 0.09409 -0.0076 0.0191 1.0000
13.750 0.9603 0.10659 0.10128 -0.0120 0.0192 1.0000
|
Polar data table (+)
Polar graphs
<< Back to PMC19 Smoothed (pmc19sm-il)