PT40 (pt40-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: PT40 (pt40-il) Reynolds number: 100,000 Max Cl/Cd: 48.75 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pt40-il-100000.txt Download as CSV file: xf-pt40-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: PT40
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3209 0.09900 0.09334 -0.0267 1.0000 0.1197
-7.500 -0.3629 0.09834 0.09286 -0.0296 1.0000 0.1222
-7.250 -0.3786 0.09524 0.08987 -0.0304 1.0000 0.1231
-7.000 -0.3386 0.09152 0.08613 -0.0258 1.0000 0.1253
-6.750 -0.3347 0.08939 0.08408 -0.0239 1.0000 0.1275
-6.500 -0.3440 0.08767 0.08247 -0.0218 1.0000 0.1297
-6.250 -0.3595 0.08584 0.08074 -0.0211 1.0000 0.1324
-6.000 -0.4141 0.08384 0.07864 -0.0290 1.0000 0.1363
-5.750 -0.4045 0.08066 0.07563 -0.0243 1.0000 0.1372
-5.500 -0.4001 0.07860 0.07367 -0.0204 1.0000 0.1384
-5.250 -0.3992 0.07684 0.07198 -0.0174 1.0000 0.1401
-5.000 -0.4003 0.07502 0.07021 -0.0156 1.0000 0.1426
-4.750 -0.4100 0.07182 0.06669 -0.0235 1.0000 0.1519
-4.500 -0.4043 0.06909 0.06411 -0.0203 1.0000 0.1531
-4.250 -0.3949 0.06706 0.06218 -0.0182 0.9992 0.1552
-4.000 -0.3535 0.06308 0.05793 -0.0282 0.9916 0.1697
-3.750 -0.3103 0.06209 0.05667 -0.0349 0.9836 0.1859
-3.500 -0.2863 0.05702 0.05182 -0.0359 0.9775 0.1894
-3.250 -0.2518 0.05467 0.04956 -0.0381 0.9713 0.1971
-3.000 -0.2102 0.05370 0.04813 -0.0455 0.9610 0.2270
-2.750 -0.1802 0.04936 0.04411 -0.0464 0.9564 0.2324
-2.500 -0.1517 0.04742 0.04217 -0.0482 0.9467 0.2536
-2.250 -0.1180 0.04551 0.04032 -0.0501 0.9396 0.2781
-2.000 -0.0878 0.04400 0.03881 -0.0517 0.9304 0.3176
-1.250 0.0869 0.03225 0.02431 -0.0713 0.9108 0.1517
-1.000 0.1173 0.03036 0.02242 -0.0720 0.9001 0.1470
-0.750 0.1660 0.02859 0.02042 -0.0753 0.8945 0.1430
-0.500 0.2031 0.02754 0.01919 -0.0765 0.8850 0.1426
-0.250 0.2499 0.02622 0.01769 -0.0791 0.8776 0.1414
0.000 0.2940 0.02490 0.01626 -0.0806 0.8664 0.1420
0.250 0.3440 0.02332 0.01463 -0.0826 0.8552 0.1460
0.500 0.3770 0.02241 0.01367 -0.0820 0.8396 0.1484
0.750 0.4119 0.02163 0.01285 -0.0819 0.8273 0.1508
1.000 0.4461 0.02054 0.01192 -0.0819 0.8152 0.1564
1.250 0.4732 0.02002 0.01148 -0.0807 0.7996 0.1621
1.500 0.5027 0.01950 0.01097 -0.0797 0.7852 0.1676
1.750 0.5334 0.01874 0.01032 -0.0789 0.7716 0.1781
2.000 0.5588 0.01837 0.01000 -0.0774 0.7538 0.1910
2.250 0.5851 0.01794 0.00970 -0.0761 0.7359 0.2169
2.500 0.6252 0.01561 0.00940 -0.0765 0.7169 1.0000
2.750 0.6510 0.01560 0.00914 -0.0749 0.6966 1.0000
3.000 0.6762 0.01560 0.00895 -0.0733 0.6747 1.0000
3.250 0.7010 0.01559 0.00877 -0.0717 0.6505 1.0000
3.500 0.7251 0.01562 0.00863 -0.0700 0.6232 1.0000
3.750 0.7477 0.01570 0.00855 -0.0681 0.5900 1.0000
4.000 0.7695 0.01586 0.00849 -0.0660 0.5503 1.0000
4.250 0.7898 0.01620 0.00850 -0.0638 0.5033 1.0000
4.500 0.8089 0.01674 0.00869 -0.0616 0.4521 1.0000
4.750 0.8285 0.01742 0.00899 -0.0597 0.4094 1.0000
5.000 0.8494 0.01814 0.00942 -0.0581 0.3763 1.0000
5.250 0.8715 0.01890 0.00989 -0.0569 0.3526 1.0000
5.500 0.8947 0.01966 0.01044 -0.0558 0.3334 1.0000
5.750 0.9184 0.02040 0.01105 -0.0549 0.3171 1.0000
6.000 0.9420 0.02115 0.01168 -0.0540 0.3021 1.0000
6.250 0.9651 0.02190 0.01231 -0.0530 0.2878 1.0000
6.500 0.9876 0.02263 0.01286 -0.0520 0.2733 1.0000
6.750 1.0093 0.02326 0.01339 -0.0509 0.2593 1.0000
7.000 1.0308 0.02391 0.01407 -0.0498 0.2469 1.0000
7.250 1.0537 0.02471 0.01477 -0.0489 0.2363 1.0000
7.500 1.0754 0.02536 0.01540 -0.0478 0.2254 1.0000
7.750 1.0962 0.02612 0.01620 -0.0466 0.2146 1.0000
8.000 1.1177 0.02692 0.01687 -0.0456 0.2039 1.0000
8.250 1.1360 0.02755 0.01754 -0.0440 0.1920 1.0000
8.500 1.1531 0.02833 0.01837 -0.0423 0.1792 1.0000
8.750 1.1691 0.02918 0.01922 -0.0405 0.1656 1.0000
9.000 1.1838 0.03013 0.02012 -0.0385 0.1519 1.0000
9.250 1.1985 0.03117 0.02113 -0.0366 0.1397 1.0000
9.500 1.2145 0.03233 0.02224 -0.0349 0.1301 1.0000
9.750 1.2340 0.03347 0.02317 -0.0338 0.1231 1.0000
10.000 1.2489 0.03482 0.02473 -0.0319 0.1167 1.0000
10.250 1.2701 0.03606 0.02579 -0.0311 0.1121 1.0000
10.500 1.2838 0.03754 0.02752 -0.0292 0.1077 1.0000
10.750 1.3030 0.03871 0.02861 -0.0282 0.1043 1.0000
11.000 1.3195 0.04044 0.03045 -0.0269 0.1014 1.0000
11.250 1.3326 0.04226 0.03248 -0.0251 0.0989 1.0000
11.500 1.3479 0.04392 0.03424 -0.0238 0.0968 1.0000
11.750 1.3679 0.04553 0.03580 -0.0231 0.0950 1.0000
12.000 1.3784 0.04779 0.03824 -0.0214 0.0936 1.0000
12.250 1.3753 0.05023 0.04103 -0.0182 0.0926 1.0000
12.500 1.3701 0.05277 0.04388 -0.0150 0.0915 1.0000
12.750 1.3634 0.05544 0.04681 -0.0122 0.0906 1.0000
13.000 1.3553 0.05829 0.04990 -0.0098 0.0898 1.0000
13.250 1.3458 0.06135 0.05318 -0.0077 0.0891 1.0000
13.500 1.3327 0.06486 0.05691 -0.0061 0.0886 1.0000
13.750 1.3074 0.06962 0.06196 -0.0052 0.0885 1.0000
14.000 1.2432 0.07896 0.07184 -0.0068 0.0895 1.0000
14.250 1.1267 0.09899 0.09248 -0.0175 0.0924 1.0000
14.500 1.0505 0.11846 0.11219 -0.0292 0.0944 1.0000
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Polar data table (+)
Polar graphs
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