SA7036 (sa7036-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7036 (sa7036-il) Reynolds number: 50,000 Max Cl/Cd: 38.47 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7036-il-50000-n5.txt Download as CSV file: xf-sa7036-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7036
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4115 0.08294 0.07643 -0.0403 1.0000 0.0461
-7.500 -0.4116 0.07941 0.07297 -0.0409 1.0000 0.0457
-7.250 -0.4125 0.07586 0.06949 -0.0413 1.0000 0.0452
-7.000 -0.4140 0.07224 0.06591 -0.0419 1.0000 0.0446
-6.750 -0.4155 0.06850 0.06218 -0.0425 1.0000 0.0439
-6.500 -0.4164 0.06467 0.05833 -0.0431 1.0000 0.0432
-6.250 -0.4157 0.06081 0.05439 -0.0436 1.0000 0.0425
-6.000 -0.4132 0.05673 0.05017 -0.0441 1.0000 0.0419
-5.750 -0.4077 0.05266 0.04587 -0.0445 1.0000 0.0413
-5.500 -0.3991 0.04855 0.04146 -0.0448 1.0000 0.0409
-5.250 -0.3870 0.04471 0.03724 -0.0449 1.0000 0.0407
-5.000 -0.3719 0.04110 0.03319 -0.0449 1.0000 0.0408
-4.750 -0.3543 0.03788 0.02949 -0.0446 1.0000 0.0415
-4.500 -0.3343 0.03512 0.02617 -0.0442 1.0000 0.0440
-4.250 -0.3124 0.03278 0.02317 -0.0435 1.0000 0.0462
-4.000 -0.2914 0.03050 0.02060 -0.0430 1.0000 0.0481
-3.750 -0.2695 0.02872 0.01858 -0.0421 1.0000 0.0501
-3.500 -0.2471 0.02721 0.01682 -0.0412 1.0000 0.0529
-3.250 -0.2246 0.02598 0.01529 -0.0401 1.0000 0.0573
-3.000 -0.2028 0.02493 0.01419 -0.0393 1.0000 0.0650
-2.750 -0.1735 0.02390 0.01296 -0.0396 0.9967 0.0751
-2.500 -0.1352 0.02277 0.01180 -0.0420 0.9895 0.1047
-2.250 -0.0965 0.02113 0.01099 -0.0451 0.9832 0.2434
-2.000 -0.0669 0.01970 0.01089 -0.0458 0.9750 0.5235
-1.750 -0.0436 0.01901 0.01099 -0.0431 0.9662 0.7693
-1.500 0.0139 0.01876 0.01049 -0.0481 0.9583 1.0000
-1.250 0.0521 0.01896 0.01025 -0.0506 0.9472 1.0000
-1.000 0.0905 0.01916 0.01007 -0.0531 0.9362 1.0000
-0.750 0.1303 0.01935 0.00992 -0.0557 0.9256 1.0000
-0.500 0.1704 0.01951 0.00981 -0.0582 0.9148 1.0000
-0.250 0.2061 0.01965 0.00973 -0.0599 0.9023 1.0000
0.000 0.2418 0.01978 0.00965 -0.0615 0.8899 1.0000
0.250 0.2764 0.01989 0.00961 -0.0628 0.8772 1.0000
0.500 0.3102 0.01998 0.00957 -0.0638 0.8642 1.0000
0.750 0.3432 0.02004 0.00951 -0.0646 0.8510 1.0000
1.000 0.3755 0.02008 0.00947 -0.0652 0.8373 1.0000
1.250 0.4071 0.02011 0.00943 -0.0656 0.8231 1.0000
1.500 0.4381 0.02013 0.00940 -0.0658 0.8084 1.0000
1.750 0.4685 0.02014 0.00937 -0.0658 0.7934 1.0000
2.000 0.4987 0.02014 0.00934 -0.0657 0.7779 1.0000
2.250 0.5287 0.02014 0.00931 -0.0655 0.7622 1.0000
2.500 0.5586 0.02012 0.00929 -0.0653 0.7462 1.0000
2.750 0.5855 0.02021 0.00937 -0.0646 0.7280 1.0000
3.000 0.6129 0.02028 0.00944 -0.0640 0.7095 1.0000
3.250 0.6412 0.02033 0.00948 -0.0634 0.6914 1.0000
3.500 0.6678 0.02046 0.00964 -0.0627 0.6716 1.0000
3.750 0.6940 0.02062 0.00980 -0.0618 0.6511 1.0000
4.000 0.7205 0.02079 0.00996 -0.0610 0.6308 1.0000
4.250 0.7455 0.02103 0.01027 -0.0601 0.6089 1.0000
4.500 0.7708 0.02129 0.01053 -0.0592 0.5873 1.0000
4.750 0.7954 0.02159 0.01084 -0.0582 0.5649 1.0000
5.000 0.8193 0.02195 0.01122 -0.0572 0.5417 1.0000
5.250 0.8436 0.02230 0.01156 -0.0562 0.5192 1.0000
5.500 0.8664 0.02275 0.01211 -0.0552 0.4954 1.0000
5.750 0.8892 0.02322 0.01262 -0.0541 0.4722 1.0000
6.000 0.9121 0.02371 0.01312 -0.0530 0.4495 1.0000
6.250 0.9337 0.02429 0.01378 -0.0519 0.4256 1.0000
6.500 0.9552 0.02489 0.01447 -0.0508 0.4024 1.0000
6.750 0.9762 0.02553 0.01513 -0.0496 0.3794 1.0000
7.000 0.9960 0.02624 0.01593 -0.0483 0.3555 1.0000
7.250 1.0155 0.02700 0.01673 -0.0470 0.3325 1.0000
7.500 1.0342 0.02780 0.01759 -0.0457 0.3100 1.0000
7.750 1.0522 0.02870 0.01857 -0.0443 0.2875 1.0000
8.000 1.0695 0.02963 0.01958 -0.0429 0.2666 1.0000
8.250 1.0853 0.03067 0.02075 -0.0414 0.2444 1.0000
8.500 1.1002 0.03176 0.02184 -0.0398 0.2244 1.0000
8.750 1.1134 0.03297 0.02319 -0.0382 0.2033 1.0000
9.000 1.1255 0.03425 0.02450 -0.0364 0.1848 1.0000
9.250 1.1362 0.03567 0.02601 -0.0346 0.1666 1.0000
9.500 1.1459 0.03722 0.02766 -0.0328 0.1502 1.0000
10.000 1.1600 0.04064 0.03133 -0.0288 0.1225 1.0000
10.250 1.1645 0.04254 0.03331 -0.0267 0.1112 1.0000
10.500 1.1672 0.04453 0.03535 -0.0248 0.1014 1.0000
10.750 1.1718 0.04677 0.03774 -0.0231 0.0928 1.0000
11.000 1.1746 0.04926 0.04045 -0.0216 0.0850 1.0000
11.250 1.1746 0.05161 0.04278 -0.0203 0.0787 1.0000
11.500 1.1754 0.05470 0.04623 -0.0191 0.0728 1.0000
11.750 1.1762 0.05763 0.04930 -0.0182 0.0683 1.0000
12.000 1.1746 0.06090 0.05269 -0.0176 0.0642 1.0000
12.250 1.1663 0.06500 0.05716 -0.0175 0.0608 1.0000
12.500 1.1581 0.06900 0.06137 -0.0180 0.0577 1.0000
12.750 1.1557 0.07256 0.06496 -0.0183 0.0550 1.0000
13.000 1.1470 0.07747 0.07006 -0.0193 0.0534 1.0000
13.250 1.1301 0.08367 0.07658 -0.0217 0.0527 1.0000
13.500 1.1112 0.09061 0.08379 -0.0250 0.0524 1.0000
13.750 1.0904 0.09841 0.09181 -0.0292 0.0524 1.0000
14.000 1.0690 0.10693 0.10051 -0.0342 0.0528 1.0000
14.250 1.0467 0.11640 0.11011 -0.0399 0.0533 1.0000
14.500 1.0244 0.12668 0.12047 -0.0461 0.0537 1.0000
14.750 1.0030 0.13772 0.13151 -0.0526 0.0540 1.0000
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Polar data table (+)
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