M6 (65%) (m665-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: M6 (65%) (m665-il) Reynolds number: 200,000 Max Cl/Cd: 60.28 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m665-il-200000.txt Download as CSV file: xf-m665-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: M6 (65%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5384 0.08674 0.08322 -0.0127 1.0000 0.0445
-8.250 -0.5460 0.08241 0.07893 -0.0166 1.0000 0.0453
-8.000 -0.5558 0.07832 0.07483 -0.0193 1.0000 0.0461
-7.750 -0.5639 0.07390 0.07025 -0.0234 1.0000 0.0472
-7.500 -0.5651 0.07048 0.06662 -0.0238 1.0000 0.0476
-7.250 -0.5699 0.06377 0.05986 -0.0238 1.0000 0.0483
-7.000 -0.5609 0.06015 0.05633 -0.0228 1.0000 0.0494
-6.750 -0.5518 0.05750 0.05368 -0.0216 1.0000 0.0508
-6.500 -0.5432 0.05462 0.05073 -0.0207 1.0000 0.0527
-6.250 -0.5345 0.05144 0.04742 -0.0197 1.0000 0.0555
-5.750 -0.5210 0.04399 0.03944 -0.0162 1.0000 0.0627
-5.500 -0.5083 0.04175 0.03717 -0.0146 1.0000 0.0653
-5.250 -0.5008 0.04026 0.03498 -0.0109 1.0000 0.0743
-5.000 -0.4874 0.03646 0.03137 -0.0098 1.0000 0.0766
-4.750 -0.4768 0.03568 0.03017 -0.0066 1.0000 0.0885
-4.500 -0.4619 0.02751 0.02095 -0.0009 1.0000 0.0480
-4.250 -0.4478 0.02375 0.01700 0.0016 1.0000 0.0449
-4.000 -0.4316 0.02146 0.01435 0.0042 1.0000 0.0442
-3.750 -0.4144 0.02035 0.01295 0.0066 1.0000 0.0465
-3.500 -0.3976 0.01945 0.01178 0.0089 1.0000 0.0478
-3.250 -0.3789 0.01733 0.00945 0.0107 1.0000 0.0491
-3.000 -0.3470 0.01633 0.00845 0.0095 0.9966 0.0539
-2.750 -0.3048 0.01527 0.00730 0.0067 0.9901 0.0575
-2.500 -0.2629 0.01415 0.00616 0.0038 0.9839 0.0624
-2.250 -0.2232 0.01344 0.00548 0.0012 0.9748 0.0716
-2.000 -0.1834 0.01262 0.00471 -0.0013 0.9665 0.0849
-1.750 -0.1470 0.01127 0.00405 -0.0034 0.9577 0.2075
-1.500 -0.0686 0.00945 0.00484 -0.0121 0.9745 0.9592
-1.250 0.0206 0.00967 0.00483 -0.0240 0.9926 1.0000
-1.000 0.0711 0.00952 0.00457 -0.0290 0.9774 1.0000
-0.750 0.1224 0.00937 0.00431 -0.0341 0.9615 1.0000
-0.500 0.1738 0.00920 0.00405 -0.0392 0.9426 1.0000
-0.250 0.2206 0.00905 0.00381 -0.0431 0.9176 1.0000
0.000 0.2569 0.00898 0.00363 -0.0448 0.8900 1.0000
0.250 0.2833 0.00900 0.00353 -0.0443 0.8630 1.0000
0.500 0.3064 0.00905 0.00346 -0.0431 0.8396 1.0000
0.750 0.3282 0.00912 0.00344 -0.0417 0.8173 1.0000
1.000 0.3502 0.00920 0.00343 -0.0404 0.7979 1.0000
1.250 0.3724 0.00929 0.00343 -0.0391 0.7796 1.0000
1.500 0.3945 0.00937 0.00346 -0.0378 0.7607 1.0000
1.750 0.4166 0.00945 0.00348 -0.0365 0.7417 1.0000
2.000 0.4388 0.00955 0.00352 -0.0352 0.7233 1.0000
2.250 0.4612 0.00964 0.00357 -0.0339 0.7049 1.0000
2.500 0.4840 0.00973 0.00365 -0.0328 0.6876 1.0000
2.750 0.5067 0.00983 0.00373 -0.0316 0.6701 1.0000
3.000 0.5292 0.00993 0.00381 -0.0303 0.6507 1.0000
3.250 0.5515 0.01002 0.00389 -0.0290 0.6283 1.0000
3.500 0.5735 0.01013 0.00395 -0.0276 0.6041 1.0000
3.750 0.5945 0.01021 0.00398 -0.0260 0.5691 1.0000
4.000 0.6154 0.01035 0.00405 -0.0244 0.5314 1.0000
4.250 0.6360 0.01055 0.00414 -0.0229 0.4849 1.0000
4.500 0.6553 0.01091 0.00427 -0.0211 0.4203 1.0000
4.750 0.6722 0.01158 0.00452 -0.0192 0.3202 1.0000
5.000 0.6788 0.01379 0.00543 -0.0163 0.0953 1.0000
5.250 0.6943 0.01511 0.00660 -0.0141 0.0608 1.0000
5.500 0.7118 0.01606 0.00756 -0.0122 0.0517 1.0000
5.750 0.7301 0.01689 0.00839 -0.0105 0.0465 1.0000
6.000 0.7451 0.01828 0.00977 -0.0082 0.0437 1.0000
6.250 0.7644 0.01923 0.01080 -0.0066 0.0421 1.0000
6.500 0.7840 0.02035 0.01201 -0.0049 0.0408 1.0000
6.750 0.8043 0.02164 0.01338 -0.0034 0.0400 1.0000
7.000 0.8254 0.02312 0.01497 -0.0020 0.0394 1.0000
7.250 0.8466 0.02478 0.01680 -0.0006 0.0389 1.0000
7.500 0.8667 0.02625 0.01841 0.0007 0.0376 1.0000
7.750 0.8861 0.02797 0.02034 0.0021 0.0367 1.0000
8.000 0.9039 0.03050 0.02323 0.0040 0.0373 1.0000
8.250 0.9175 0.03382 0.02704 0.0065 0.0388 1.0000
8.500 0.9269 0.03786 0.03153 0.0092 0.0411 1.0000
12.500 0.6200 0.11996 0.11638 0.0089 0.0682 1.0000
12.750 0.5994 0.12628 0.12266 0.0037 0.0676 1.0000
|
Polar data table (+)
Polar graphs
<< Back to M6 (65%) (m665-il)