Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf) Reynolds number: 100,000 Max Cl/Cd: 33.87 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0009-jf-100000.txt Download as CSV file: xf-joukowsk0009-jf-100000.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=9%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7124 0.11182 0.10693 0.0229 1.0000 0.1469
-9.750 -0.8126 0.07698 0.07214 -0.0056 1.0000 0.0796
-9.500 -0.8146 0.07199 0.06708 -0.0067 1.0000 0.0771
-9.250 -0.8251 0.06641 0.06141 -0.0085 1.0000 0.0757
-9.000 -0.8393 0.05996 0.05474 -0.0106 1.0000 0.0736
-8.750 -0.8536 0.05251 0.04678 -0.0122 1.0000 0.0708
-8.500 -0.8628 0.04480 0.03810 -0.0127 1.0000 0.0682
-8.250 -0.8508 0.04051 0.03332 -0.0123 1.0000 0.0685
-8.000 -0.8325 0.03746 0.03003 -0.0120 1.0000 0.0703
-7.750 -0.8130 0.03502 0.02727 -0.0115 1.0000 0.0740
-7.500 -0.7930 0.03226 0.02389 -0.0108 1.0000 0.0772
-7.250 -0.7710 0.02926 0.02049 -0.0103 1.0000 0.0801
-7.000 -0.7472 0.02753 0.01874 -0.0099 1.0000 0.0860
-6.750 -0.7226 0.02571 0.01653 -0.0093 1.0000 0.0924
-6.500 -0.6978 0.02390 0.01481 -0.0089 1.0000 0.1000
-6.250 -0.6730 0.02239 0.01324 -0.0084 1.0000 0.1105
-6.000 -0.6480 0.02097 0.01180 -0.0078 1.0000 0.1231
-5.750 -0.6234 0.01976 0.01067 -0.0073 1.0000 0.1407
-5.500 -0.5989 0.01854 0.00954 -0.0068 1.0000 0.1641
-5.250 -0.5749 0.01741 0.00862 -0.0063 1.0000 0.1962
-5.000 -0.5510 0.01640 0.00785 -0.0057 1.0000 0.2399
-4.750 -0.5270 0.01556 0.00725 -0.0052 1.0000 0.2928
-4.500 -0.5030 0.01488 0.00685 -0.0046 1.0000 0.3453
-4.250 -0.4784 0.01438 0.00650 -0.0039 1.0000 0.3975
-4.000 -0.4539 0.01396 0.00627 -0.0031 1.0000 0.4446
-3.750 -0.4293 0.01362 0.00606 -0.0022 1.0000 0.4890
-3.500 -0.4049 0.01332 0.00590 -0.0012 1.0000 0.5299
-3.250 -0.3807 0.01306 0.00577 -0.0001 1.0000 0.5685
-3.000 -0.3567 0.01282 0.00565 0.0011 1.0000 0.6060
-2.750 -0.3331 0.01260 0.00555 0.0025 1.0000 0.6415
-2.500 -0.3102 0.01240 0.00546 0.0040 1.0000 0.6749
-2.250 -0.2882 0.01221 0.00539 0.0057 1.0000 0.7078
-2.000 -0.2673 0.01204 0.00533 0.0077 1.0000 0.7401
-1.750 -0.2479 0.01187 0.00528 0.0099 1.0000 0.7723
-1.500 -0.2303 0.01172 0.00522 0.0124 1.0000 0.8050
-1.250 -0.2141 0.01159 0.00520 0.0152 1.0000 0.8382
-1.000 -0.1982 0.01150 0.00520 0.0181 1.0000 0.8733
-0.750 -0.1751 0.01146 0.00524 0.0193 1.0000 0.9134
-0.500 -0.1256 0.01154 0.00532 0.0153 1.0000 0.9502
-0.250 -0.0572 0.01160 0.00535 0.0073 1.0000 0.9784
0.000 0.0000 0.01154 0.00529 0.0000 1.0000 1.0000
0.250 0.0573 0.01160 0.00535 -0.0073 0.9783 1.0000
0.500 0.1256 0.01154 0.00532 -0.0153 0.9502 1.0000
0.750 0.1751 0.01146 0.00523 -0.0193 0.9134 1.0000
1.000 0.1983 0.01150 0.00521 -0.0181 0.8733 1.0000
1.250 0.2142 0.01159 0.00520 -0.0152 0.8382 1.0000
1.500 0.2304 0.01172 0.00522 -0.0124 0.8049 1.0000
1.750 0.2480 0.01187 0.00528 -0.0099 0.7723 1.0000
2.000 0.2674 0.01204 0.00533 -0.0077 0.7402 1.0000
2.250 0.2883 0.01221 0.00539 -0.0057 0.7078 1.0000
2.500 0.3103 0.01240 0.00546 -0.0040 0.6749 1.0000
2.750 0.3332 0.01260 0.00555 -0.0025 0.6414 1.0000
3.000 0.3568 0.01282 0.00565 -0.0012 0.6059 1.0000
3.250 0.3808 0.01306 0.00577 0.0000 0.5685 1.0000
3.500 0.4050 0.01332 0.00590 0.0012 0.5298 1.0000
3.750 0.4294 0.01362 0.00606 0.0022 0.4890 1.0000
4.000 0.4540 0.01396 0.00627 0.0031 0.4446 1.0000
4.250 0.4785 0.01438 0.00650 0.0039 0.3975 1.0000
4.500 0.5030 0.01488 0.00685 0.0046 0.3453 1.0000
4.750 0.5270 0.01556 0.00725 0.0052 0.2928 1.0000
5.000 0.5511 0.01640 0.00785 0.0057 0.2399 1.0000
5.250 0.5749 0.01741 0.00862 0.0063 0.1962 1.0000
5.500 0.5989 0.01853 0.00954 0.0068 0.1641 1.0000
5.750 0.6234 0.01976 0.01067 0.0073 0.1407 1.0000
6.000 0.6480 0.02096 0.01180 0.0078 0.1231 1.0000
6.250 0.6730 0.02239 0.01324 0.0084 0.1104 1.0000
6.500 0.6978 0.02390 0.01481 0.0089 0.0999 1.0000
6.750 0.7224 0.02571 0.01653 0.0093 0.0924 1.0000
7.000 0.7471 0.02752 0.01874 0.0099 0.0860 1.0000
7.250 0.7709 0.02927 0.02049 0.0103 0.0800 1.0000
7.500 0.7929 0.03225 0.02388 0.0109 0.0772 1.0000
7.750 0.8128 0.03500 0.02725 0.0116 0.0740 1.0000
8.000 0.8324 0.03741 0.02995 0.0120 0.0702 1.0000
8.250 0.8504 0.04049 0.03330 0.0124 0.0685 1.0000
8.500 0.8624 0.04477 0.03806 0.0128 0.0682 1.0000
8.750 0.8529 0.05255 0.04684 0.0123 0.0710 1.0000
9.000 0.8389 0.05995 0.05472 0.0107 0.0736 1.0000
9.250 0.8251 0.06639 0.06139 0.0086 0.0757 1.0000
9.500 0.8152 0.07193 0.06703 0.0068 0.0771 1.0000
9.750 0.8113 0.07711 0.07221 0.0056 0.0780 1.0000
10.000 0.7120 0.11186 0.10697 -0.0232 0.1468 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Joukovsky f=0% t=9% (joukowsk0009-jf)