TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: TSAGI 8% AIRFOIL (tsagi8-il) Reynolds number: 50,000 Max Cl/Cd: 32.48 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi8-il-50000-n5.txt Download as CSV file: xf-tsagi8-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TSAGI 8% AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4610 0.09724 0.09089 -0.0110 1.0000 0.0480
-9.250 -0.4631 0.09265 0.08630 -0.0130 1.0000 0.0450
-9.000 -0.5580 0.09743 0.09072 -0.0118 1.0000 0.0453
-8.750 -0.5553 0.09321 0.08654 -0.0125 1.0000 0.0440
-8.500 -0.5563 0.08891 0.08230 -0.0147 1.0000 0.0430
-8.250 -0.5604 0.08450 0.07794 -0.0168 1.0000 0.0420
-8.000 -0.5649 0.08019 0.07366 -0.0183 1.0000 0.0410
-7.750 -0.5678 0.07570 0.06915 -0.0199 1.0000 0.0399
-7.500 -0.5700 0.07103 0.06441 -0.0211 1.0000 0.0388
-7.250 -0.5719 0.06601 0.05924 -0.0218 1.0000 0.0377
-6.750 -0.5677 0.05670 0.04918 -0.0210 1.0000 0.0355
-6.500 -0.5608 0.05277 0.04493 -0.0197 1.0000 0.0356
-6.250 -0.5521 0.04916 0.04121 -0.0186 1.0000 0.0366
-6.000 -0.5402 0.04649 0.03841 -0.0173 1.0000 0.0388
-5.750 -0.5281 0.04332 0.03488 -0.0156 1.0000 0.0403
-5.500 -0.5144 0.04009 0.03120 -0.0138 1.0000 0.0412
-5.250 -0.4987 0.03690 0.02745 -0.0117 1.0000 0.0419
-5.000 -0.4805 0.03395 0.02398 -0.0098 1.0000 0.0430
-4.750 -0.4596 0.03152 0.02091 -0.0079 1.0000 0.0460
-4.500 -0.4399 0.02934 0.01863 -0.0068 1.0000 0.0510
-4.250 -0.4156 0.02723 0.01617 -0.0055 1.0000 0.0556
-4.000 -0.3909 0.02543 0.01417 -0.0045 1.0000 0.0638
-3.750 -0.3648 0.02389 0.01243 -0.0036 1.0000 0.0759
-3.500 -0.3391 0.02257 0.01099 -0.0031 1.0000 0.0950
-3.250 -0.3148 0.02121 0.00960 -0.0023 1.0000 0.1216
-3.000 -0.2947 0.01989 0.00851 -0.0010 1.0000 0.1722
-2.750 -0.1651 0.01691 0.00803 -0.0167 1.0000 0.9604
-2.500 -0.0904 0.01669 0.00709 -0.0263 1.0000 1.0000
-2.250 -0.0733 0.01655 0.00669 -0.0248 1.0000 1.0000
-2.000 -0.0568 0.01645 0.00640 -0.0232 1.0000 1.0000
-1.750 -0.0413 0.01639 0.00617 -0.0213 1.0000 1.0000
-1.500 -0.0270 0.01638 0.00603 -0.0193 1.0000 1.0000
-1.250 -0.0140 0.01642 0.00593 -0.0172 1.0000 1.0000
-1.000 -0.0030 0.01652 0.00594 -0.0147 1.0000 1.0000
-0.750 0.0057 0.01669 0.00603 -0.0119 1.0000 1.0000
-0.500 0.0122 0.01694 0.00620 -0.0089 1.0000 1.0000
-0.250 0.0601 0.01706 0.00619 -0.0139 0.9804 1.0000
0.000 0.1063 0.01718 0.00622 -0.0182 0.9625 1.0000
0.250 0.1523 0.01725 0.00624 -0.0224 0.9449 1.0000
0.500 0.1978 0.01729 0.00627 -0.0263 0.9275 1.0000
0.750 0.2394 0.01733 0.00631 -0.0293 0.9087 1.0000
1.000 0.2776 0.01737 0.00640 -0.0315 0.8889 1.0000
1.250 0.3145 0.01742 0.00648 -0.0332 0.8701 1.0000
1.500 0.3447 0.01754 0.00663 -0.0336 0.8492 1.0000
1.750 0.3746 0.01765 0.00680 -0.0337 0.8298 1.0000
2.000 0.4004 0.01783 0.00706 -0.0332 0.8096 1.0000
2.250 0.4256 0.01801 0.00732 -0.0324 0.7900 1.0000
2.500 0.4503 0.01820 0.00758 -0.0314 0.7716 1.0000
2.750 0.4729 0.01846 0.00799 -0.0302 0.7517 1.0000
3.000 0.4961 0.01870 0.00835 -0.0289 0.7329 1.0000
3.250 0.5192 0.01895 0.00873 -0.0276 0.7147 1.0000
3.500 0.5410 0.01925 0.00920 -0.0262 0.6949 1.0000
3.750 0.5636 0.01953 0.00971 -0.0248 0.6757 1.0000
4.000 0.5862 0.01982 0.01020 -0.0234 0.6560 1.0000
4.250 0.6083 0.02013 0.01074 -0.0219 0.6344 1.0000
4.500 0.6304 0.02042 0.01128 -0.0202 0.6118 1.0000
4.750 0.6501 0.02058 0.01173 -0.0178 0.5805 1.0000
5.000 0.6609 0.02035 0.01133 -0.0128 0.5048 1.0000
5.250 0.6678 0.02076 0.01113 -0.0081 0.3674 1.0000
5.500 0.6692 0.02346 0.01217 -0.0047 0.1262 1.0000
5.750 0.6786 0.02603 0.01425 -0.0023 0.0766 1.0000
6.000 0.6916 0.02778 0.01605 -0.0001 0.0600 1.0000
6.250 0.7037 0.02963 0.01792 0.0022 0.0534 1.0000
6.500 0.7201 0.03116 0.01973 0.0044 0.0466 1.0000
6.750 0.7355 0.03309 0.02174 0.0062 0.0418 1.0000
7.000 0.7583 0.03513 0.02406 0.0079 0.0393 1.0000
7.250 0.7810 0.03743 0.02666 0.0093 0.0370 1.0000
7.500 0.8000 0.03974 0.02918 0.0106 0.0343 1.0000
7.750 0.8162 0.04275 0.03235 0.0119 0.0321 1.0000
8.000 0.8305 0.04578 0.03589 0.0138 0.0314 1.0000
8.250 0.8409 0.04906 0.03964 0.0157 0.0311 1.0000
8.500 0.8471 0.05255 0.04357 0.0176 0.0309 1.0000
8.750 0.8492 0.05612 0.04754 0.0196 0.0308 1.0000
9.000 0.8477 0.05975 0.05151 0.0214 0.0309 1.0000
9.250 0.8424 0.06337 0.05542 0.0231 0.0310 1.0000
9.500 0.8319 0.06706 0.05936 0.0247 0.0309 1.0000
9.750 0.8193 0.07043 0.06289 0.0261 0.0311 1.0000
10.000 0.8036 0.07413 0.06671 0.0266 0.0312 1.0000
10.250 0.7890 0.07829 0.07096 0.0256 0.0315 1.0000
10.500 0.7741 0.08310 0.07586 0.0235 0.0317 1.0000
10.750 0.7611 0.08843 0.08123 0.0206 0.0319 1.0000
11.000 0.7496 0.09415 0.08698 0.0173 0.0321 1.0000
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Polar data table (+)
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